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Full text of "Index of NACA technical publications, June, 1954 - May, 1955"

NATIONAL ADVISORY 
COMMITTEE FOR 
AERONAUTICS 



(NaSA-TM-809<Jni -r..^ 

.PUBLlCaTlONS, JaNE fj^?^ ^^'^^^ TECHNICAL 

1 (National Adiisorv'r ^^ ' ^^^' ^955 Nao-734a3 



Unci as 
00/01 20021 



INDEX DF NACA TECHNICAL PUBLICATIONS 



June, 1954 - May, 1955 




WASHINGTON - 1955 



PREFACE 



This Index of NACA Technical Publications covers those 
NACA research reports issued in the period of June 1954 
through May 1955. It is the fourth supplement to the basic 
1915-1949 Index. 

The research reports issued prior to June 1954 which have 
been declassified since that date have also been included. 
In addition, current announcement of newly declassified ma- 
terials is regularly made in the NACA Research Abstracts . 

The arrangement of the present Index follows that of its 
predecessors: (1) A classified listing of the subject cate- 
gories, (2) a chronological listing of the NACA research re- 
ports under each subject category, (3) an alphabetical index 
to the subject categories, and (4) an author index. An Ex- 
planatory Chart on page iii maybe helpful in identifying ref- 
erences to NACA research reports encountered in the liter- 
ature. 

Entries included herein duplicate in part the information 
of the index cards furnished with the individual research re- 
ports. Recipients maintaining card files may care to dis- 
card those index cards on hand for unclassified research 
reports issued during the June 1954 - May 1955 period. 

Newly available research reports are currently announced 
in the NACA Research Abstracts and are normally available 
for a period of five years after announcement. Older re- 
search reports (those issued prior to May 1950) are thus 
available on a "loan only" basis within the United States. 
Requests for NACA research reports should be forwarded 
to the address given below. 



Division of Research Information 

National Advisory Committee for Aeronautics 

1512 H Street, N. W. 

Washington 25, D. C. 

November 1, 1955 



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Subject 




Subject 




Heading 




Heading 




Number 


Subject Heading Outline 


Number 


Subject Heading Outline 


1 


AERODYNAMICS 


1.2.2,7 


Wake 






1, 2. 2. 8 


Bovmdary Layer 


1.1 


Fundamental Aerodynamics 


1.2.2.8.1 


Characteristics 


1.1.1 


Incompressible Flow 


1.2.2.8.2 


Control 


1.1.2 


Compressible Flow 






1.1.2.1 


Subsonic Flow 


1.3 


Bodies 


1.1.2.2 


Mixed Flow 


1.3.1 


Theory 


1.1.2.3 


Supersonic Flow 


1.3.2 


Shape Variables 


1.1.3 


Viscous Flow 


1.3,2,1 


Fineness Ratio 


1.1.3.1 


Laminar Flow 


1,3.2.2 


Cross Section 


1.1.3.2 


Turbulent Flow 


1.3.2.3 


Thickness Distribution 


1.1.3.3 


Jet Mixing 


1.3.2,4 


Surface Conditions 


1.1.4 


Aerodynamics With Heat 


1,3.2.5 


Protuberances 


1.1.4.1 


Heating 


1.3.3 


Canopies 


1.1.4.2 


Heat Transfer 


1.3.4 


Ducted Bodies 


1.1.4.3 


Additions of Heat 


1.3,4,1 


Nose Shape 


1.1.5 


Flow of Rarefied Gases 


1.3.4.3 


Side Inlets 






1.3.4,4 


Side Exits 


1.2 


Wings 


1,3.5 


Hulls 


1.2.1 


Wing Sections 






1. 2. 1. 1 


Section Theory 


1.4 


Internal Aerodynamics 


1.2.1.2 


Section Variables 


1.4.1 


Air Inlets 


1.2.1.2.1 


Camber 


1.4.1.1 


Nose, Central 


1.2.1.2.2 


Thickness 


1-. 4. 1. 1. 1 


Propeller-Spinner-Cowl 


1.2.1.2.3 


Thickness Distribution 




Combinations 


1. 2. 1. 2. 4 


Inlets and Exits 


1.4.1.1.2 


Subsonic 


1. 2. 1. 2. 5 


Surface Conditions 


1.4.1.1.3 


Supersonic 


1.2.1.3 


Designated Profiles 


1.4.1.2 


Nose, Annular 


1.2.1.4 


High-Lift Devices 


1.4.1.3 


Wing Leading Edge 


1.2.1.4.1 


Plain Flaps 


1.4.1.4 


Side 


1.2.1.4.2 


Split Flaps 


1.4.1.4.1 


Scoops 


1.2.1.4.4 


Leading-Edge Flaps 


1.4.1.4.2 


Submerged 


1. 2. 1. 5 


Controls 


1.4.2 


Ducts 


1.2.1.5.1 


Flap Type 


1.4.2.1 


Diffusers 


1.2.1.5.2 


Spoilers 


1.4.2.1.1 


Subsonic 


1.2.1.6 


Boundary Layer 


1.4.2.1.2 


Supersonic 


1.2.1.6.1 


Characteristics 


1.4.2.2 


Nozzles 


1.2.1.6.2 


Control 


1.4.2.3 


Pipes 


1.2.1,7 


Reynolds Number Effects 


1.4.2.4 


Bends 


1.2.1.8 


Mach Number Effects 


1.4.3 


Exits 


1.2.1.9 


Wake 


1.4.4 


Jet Pumps and Thrust 


1.2.2 


Complete Wings 




Augmentors 


1. 2. 2. 1 


Wing Theory 


1.4.5 


Cascades 


1.2.2,2 


Wing Variables 


1.4.5,1 


Theory 


1.2.2.2.1 


Profiles 


1,4,5,2 


E3q)eriment 


1.2.2.2.2 


Aspect Ratio 


1.4.7 


Boundary Layer 


1. 2. 2. 2. 3 


Sweep 


1.4.7.1 


Characteristics 


1,2.2,2.4 


Taper and Twist 


1.4.7.2 


Control 


1. 2. 2. 2. 6 


Surface Conditions 






1.2.2.2.7 


Dihedral 


1.5 


Propellers 


1.2.2.3 


High-Lift Devices 


1,5,1 


Theory 


1. 2. 2. 3. 1 


Trailing-Edge Flaps 


1.5.2 


Design Variables 


1. 2. 2. 3. 2 


Slots and Slats 


1. 5. 2. 1 


Blade Sections 


1.2.2.3.3 


Leading-Edge Flaps 


1.5.2.4 


Blade Plan Forms 


i.2.2.4 


Controls 


1.5.2.5 


Mach Number Effects 


1.2.2.4.1 


Flap Type 


1.5.2.6 


Pusher 


1.2.2.4.2 


Spoilers 


1. 5. 2. 7 


Dual Rotation 


1.2.2.4.3 


All-Movable 


1.5.2.8 


Interference of Bodies 


1.2.2.5 


Reynolds Nimiber Effects 


1.5.2.9 


Pitch and Yaw 


1. 2, 2. 6 


Mach Number Effects 


1.5.3 


Designated Tjnpes 



Subject 




Heading 




Number 


Subject Heading Outline 


1.5.4 


Slipstream 


1.5.6 


Operating Conditions 


1.5.7 


Propeller -Spinner -Cowl 




Combinations 


1.6 


Rotating Wings 


1.6.1 


Theory 


1.6.2 


Ejqjerimental Studies 


1.6.2.1 


Power-Driven 


1.7 


Aircraft 


1.7.1 


Airplanes 


1.7.1.1 


Components in Combination 


1.7.1.1.1 


Wing-Fuselage 


1.7.1.1.2 


Wing-Nacelle 


1.7.1.1.3 


Tail-Wing and Fuselage 


1.7.1.1.5 


External Stores 


1.7.1.2 


Specific Airplanes 


1.7.1.3 


Performa.nce 


1.7.2 


Missiles 


1. 7. 2. 1 


Components in Combination 


1.7.2.1.1 


Wing-Body 


1.7.2.1.2 


Tail-Body 


1.7.2.1.3 


Jet Interference 


1.7.2.1.4 


Wing-Tail-Body 


1.7.2.2 


Specific Missiles 


1.7.3 


Rotating-Wing Aircraft 


1. 7. 3. 1 


Autogiros 


1.7.3.2 


Helicopters 


1.7.4 


Seaplanes 


1.7.4.1 


General Studies 


1.8 


Stability and Control 


1.8.1 


Stability 


1.8.1.1 


Static 


1.8.1.1.1 


Longitudinal 


1.8.1.1.2 


Lateral 


1.8.1.1.3 


Directional 


1.8.1.2 


Dynamic 


1.8.1.2.1 


Longitudinal 


1.8.1.2.2 


Lateral and Directional 


1.8.1.2.3 


Damping Derivatives 


1.8.2 


Control 


1.8.2.1 


Longitudinal 


1.8.2.2 


Lateral 


1.8.2.3 


Directional 


1.8.2.4 


Air Brakes 


1.8.2.5 


Hinge Moments 


1.8.2.6 


Automatic 


1.8.3 


Spinning 


1.8.4 


Stalling 


1.8.5 


Flying Qualities 


1.8.6 


Mass and Gyroscopic Probler 


1.8.7 


Tumbling 


1.8.8 


Automatic Stabilization 


1.9 


Aeroelasticity 


1.10 


Parachutes 



Subject 
Heading 




Number 


Subject Heading Outline 


2 


HYDRODYNAMICS 


2.1 


Theory 


2.2 


General Arrangement Studies 


2.3 


Seaplane Hull Variables 


2.3.1 


Length-Beam Ratio 


2.3.2 


Dead Rise 


2.3.3 


Steps 


2.3.6 


Chines 


2.6 


Planing Surfaces 


2.7 


Hydrofoils 


2.8 


Surface Craft 


2.10 


Stability and Control 


2. 10. 1 


Longitudinal 


3 


PROPULSION 


3.1 


Complete Systems 


3.1.1 


Reciprocating Engines 


3.1.3 


Turbojet Engines 


3.1.4 


Turbo-Propeller Engines 


3.1.1 


Ram -Jet Engines 


3.1.8 


Rocket Engines 


3.1.9 


Jet -Driven Rotors 


3. 1. 10 


Nuclear-Energy Systems 


3. 1. 12 


Comparison of Engine Types 


3.2 


Control of Engines 


3.2.2 


Control of Turbojet Engines 


3.2.3 


Control of Turbine -Ram -Jet 



3.2.4 



Engines 
Control of Turbine-Propeller 
Engines 



3.3 


Auxiliary Booster Systems 


3.3.2 


Gas Turbines 


3.3.2.1 


Liquid Injection 


3.3.2.2 


Afterburning 


3.4 


Fuels 


3.4.2 


Physical and Chemical 




Properties 


3.4.3 


Relation to Engine Performance 


3.4.3.2 


Turbine Engines, Ram Jets, 




and Pulse Jets 


3.4.3.3 


Rockets (Includes Fuel and 




Oxidant) 


3.5 


Combustion and Combustors 


3.5.1 


General Combustion Research 


3.5.1.1 


Laminar-Flow Combustion 


3.5.1.2 


Turbulent- Flow Combustion 


3.5.1.4 


Effects of Fuel Atomization 


3.5.1.5 


Reaction Mechanisms 


3.5.1.6 


Ignition of Gases 


3.5.2 


Effect of Engine Operating 




Conditions and Combustion 




Chamber Geometry 


3.5.2.2 


Turbine Engines 



VI 



Subject 




Subject 




Heading 




Heading 




Number 


Svibject Heading Outline 


Number 


Subject Heading Outline 


3.5.2.3 


Ram -Jet Engines 


4 


AIRCRAFT LOADS AND 


3.5.2.5 


Rocket Engines 




CONSTRUCTION 


3.6 


Compression and Compressors 


4.1 
4 11 


Loads 
Aerodynamic 
Wings 
Steady Loads 
Maneuvering 
Gust Loads 


3.6.1 


Flow Theory and Experiment 


4. 1. 1. 1 


3.6.1.1 
3.6.1.2 
3.6.1.3 


Axial Flow 
Radial Flow 
Mixed Flow 


4. 1. 1. 1. 1 
4. 1. 1. 1. 2 
4.1.1.1.3 


3.6.2 


Stress and Vibration 


4.1.1.2 


Tail 


3.6.3 


Matching 


4.1.1.2.1 


Steady Loads 






4. 1. 1. 2. 2 


Maneuvering 


3.7 


Turbines 


4.1.1.2.3 


Buffeting and Gust 


3.7.1 


Flow Theory and Experiment 


4. 1. 1. 3 


Fuselage, Nacelles, and 


3.7.1.1 


Axial Flow 




Canopies 


3.7.1.2 


Radial Flow 


4.1.1.4 


Rotating Wings 


3.7.2 


Cooling 


4.1.1.5 


Aeroelasticity 


3.7.3 


Stress and Vibration 


4.1.2 


Landing 


3.7.4 


Matching 


4.1.2.1 


Impact 






4.1.2.1.1 


Land 






4.1.2.1.2 


Water 


3.8 


Friction and Lubrication 


4.1.2.2 


Ground-Run 


3.8.1 


Theory and Experiment 


4.1.2.2.1 


Land 


3.8.1.1 


Hydrodynamic Theory 


4.1.2.3 


Prelanding Conditions 


3.8.1.2 


Chemistry of Lubrication 






3.8.1.3 


Surface Conditions 


4.2 


Vibration and Flutter 


3.8.2 


Sliding Contact Surfaces 


4.2.1 


Wings and Ailerons 


3. 8. 2. 1 


Sleeve Bearings 


4.2.2 


Tails 


3.8.3 


Rolling Contact Surfaces 


4.2.2.1 


Elevators and Rudders 


3.8.3.1 


Antifriction Bearings 


4.2.3 


Bodies 


3.8.4 


Sliding and Rolling Contact 


4.2.4 


Propeller, Fans, and 




Surfaces 




Compressors 


3.8.5 


Lubricants 


4.2.5 


Rotating-Wing Aircraft 



3.9 

3.9.1 

3.9.2 



3.10 
3. 10. 2 
3. 10. 3 



Heat Transfer 
Theory and Experiment 
Heat Exchangers 



Cooling of Engines 
Gas -Turbine Systems 
Ram Jets 



3,11 


Properties of Gases 


3.11.1 


Kinetic 


3. 11. 2 


Thermodynamic 


3.12 


Accessories and Accessory 




Functions 


3. 12. 1 


Fuel Systems 


3.12.1.8 


Rocket Engines 


3. 12. 2 


Ignition Systems 


3.12.5 


Cooling Systems 



4.3 

4.3.1 

4.3.2 



3.3 
3.3.1 
3. 3. 1. 1 
3.3.1.2 
3.3.2 
3.3.2.1 
4.3.4 
4.3.4.1 
4.3.5 
5.1 
5.1.1 
6 
6.1 



3.13 



Vibration and Flutter 



4.3 

4.3 

■4.3 

4.3 

4.3.6 

4.3.7 

,3 

,3 
3 

,3 



4. 
4. 
4. 
4. 



7.2 
7.3 

7.4 
7.5 



Structure^ 
Columns 
Frames, Gridworks, and 

Trusses 
Plates 
Flat 
Unstiffened 
Stiffened 
Curved 
Unstiffened 
Beams 
Box 
Shells 
Cylinders 
Circular 
Connections 
Bolted 
Riveted 
Loads and Stresses 
Compression 
Bending 
Torsion. 
Shear 



vii 



Subject 




'Heading 




Number 


Subject Heading Outline 


4.3.7.6 


Concentrated 


4.3.7.7 


Dynamic 


4.3.7.7.1 


Repeated 


4.3.7.7.2 


Transient 


4.3.7.8 


Normal Pressures 


5 


MATERIALS 


5.1 


Types 


5.1.1 


Aluminum 


5.1.3 


Steels 


5.1.4 


Heat-Resisting Alloys 


5. 1. 5 


Ceramics 


5.1.6 


Plastics 


5.1.7 


Woods 


5.1.8 


Adhesives 


5.1.9 


Protective Coatings 


5.1.11 


Sandwich and Laminates 


5.1.12 


Ceramals 


5.2 


Properties 


5.2.1 


Tensile 


5.2.2 


Compressive 


5.2.3 


Creep 


5.2.4 


Stress -Rupture 


5.2,5 


Fatigue 


5.2.6 


Shear 


5.2.7 


Flexural 


5.2.8 


Corrosion Resistance 


5.2.9 


Structure 


5.2.11 


Thermal 


5.2.12 


Multiaxial Stress 


5.2.13 


Plasticity 



5.3 



Operating Stresses and 
Conditions 



METEOROLOGY 



6.1 


Atmosphere 


6.1.2 


Gusts 


6.1.2.1 


Structure 


6. 1. 2. 3 


Turbulence 


6.1.2.4 


Alleviation 


6.2 


Ice Formation 



Subject 

Heading 

Number 


Subject Heading Outline 


7 


OPERATING PROBLEMS 


7.1 
7.1.1 


Safety 
Pilot-Escape Techniques 


7.3 

7.3.2 

7.3.3 

7.3.4 

7.3.5 

7.3.6 


Ice Prevention and Removal 
Propellers 
Wings and Tails 
Windshields 

Miscellaneous Accessories 
Propulsion Systems 


7.4 


Noise 


7.7 


Piloting Techniques 


7.8 


Physiological 


7.9 


Fire Hazards 


7.10 


General 


8 


INSTRUMENTS 


8.1 


Flight 


8.2 


Laboratory 


8.3 


Meteorological 


9 


RESEARCH EQUIPMENT AND 
TECHNIQUES 


9.1 

9.1.1 

9.1.2 

9.1.4 

9.1.5 

9.1.6 


Equipment 
Wind Tunnels 
Free-Flight 

Propulsion Research Equipment 
Propeller 
Materials 


9.2 

9.2.1 

9.2.2 

9.2.3 

9.2.4 

9.2.5 

9.2.6 

9.2.7 


Technique 
Corrections 
Aerodynamics 
Hydrodynamics 
Loads and Construction 
Propulsion 
Operating Problems 
Mathematics 



Vlll 



i 



AERODYNAMICS 

(1) 



AERODYNAMICS 1 



Fundamental 

(1.1) 



A VKCTOR STUDY OF LINEARIZED SUPERSONIC 
FLOW APPLICATIONS TO NONPLANAR 
PROBLEMS. John C. Martin. 1953. ii, 34p. 
diagrs., tab. (NACA Rept. 1143. Formerly 
TN 2641) 



INCOMPRESSIBLE FLOW 
(1.1. l) 



DIRECT MEASUREMENTS OF SKIN FRICTION. 
Satish Dhawan, California Institute of Technology. 
1953. ii, 20p. diagrs., photos. (NACA Rept. 1121. 
Formerly TN 2567) 



DIFFUSION OF HEAT FROM A LINE SOURCE IN 
ISOTROPIC TURBULENCE. Mahinder S. Uberoi 
and Stanley Corrsin, Johns Hopkins University. 
1953, ii, 29p. diagrs., photos., tab. (NACA 
Rept. 1142. Formerly TN 2710) 



AVERAGE SKIN-FRICTION DRAG COEFFICIENTS 
FROM TANK TESTS OF A PARABOLIC BODY OF 
REVOLUTION (NACA RM-10). Elmo J. Mottard and 
J. Dan Loposer. 1954. ii, 7p. diagrs., photos. 
(NACA Rept. 1161. Formerly TN 2854) 



A NOTE ON SECONDARY FLOW IN ROTATING 
RADIAL CHANNELS. James J. Kramer and John 
D. Stanitz. 1954. ii, 12p. diagrs. (NACA 
Rept. 1179. Formerly TN 3013) 



PRELIMINARY MEASUREMENTS OF TURBULENCE 
AND TEMPERATURE FLUCTUATIONS BEHIND A 
HEATED GRID. A. L. Klstler, V. O'Brien and S. 
Corrsin, Johns Hopkins University. June 1954. 
24p. diagrs., photo. (NACA RM 54D19) 



A NEW HODOGRAPH FOR FREE -STREAMLINE 
THEORY. Anatol Roshko, California Institute of 
Technology. July 1954. 39p. diagrs., 3 tabs. 
(NACA TN 3168) 



ON THE DRAG AND SHEDDING FREQUENCY OF 
TWO-DIMENSIONAL BLUFF BODIES. Anatol 
Roshko, California Institute of Technology. 
July 1954. 29p. diagrs., tab. (NACA TN 3169) 



HEAT, MASS, AND MOMENTUM TRANSFER FOR 
FLOW OVER A FLAT PLATE WITH BLOWING OR 
SUCTION. H. S. Mickley, R. C. Ross, A. L. Squyers 
and W. E. Stewart, Massachusetts Institute of 
Technology. July 1954. ii, 149p. diagrs., photos., 
9 tabs. (NACA TN 3208) 



APPLICATION OF TWO-DIMENSIONAL VORTEX 
THEORY TO THE PREDICTION OF FLOW FIELDS 
BEHIND WINGS OF WING-BODY COMBINATIONS 
AT SUBSONIC AND SUPERSONIC SPEEDS. Arthur 
Wm. Rogers. September 1954. (ii), 91p. diagrs., 
photo., 3 tabs. (NACA TN 3227) 



SUBSONIC EDGES IN THIN-WING AND SLENDER- 
BODY THEORY. Milton D. Van Dyke. November 
1954. 26p. diagrs. (NACA TN 3343) 



PREDICTION OF LOSSES INDUCED BY ANGLES OF 
ATTACK IN CASCADES OF SHARP -NOSED BLADES 
FOR INCOMPRESSIBLE AND SUBSONIC COMPRES- 
SIBLE FLOW. James J. Kramer and John D. 
Stanitz. January 1955. 45p. diagrs. (NACA 
TN 3149) 



DESCRIPTION AND ANALYSIS OF A ROCKET - 
VEHICLE EXPERIMENT ON FLUTTER INVOLVING 
WING DEFORMATION AND BODY MOTIONS. H. J. 
Cunningham and R. R. Lundstrom. January 1955. 
26p. diagrs., photos., 2 tabs. (NACA TN 3311. 
Formerly RM L50I29) 



INVESTIGATION OF THE TURBULENT BOUNDARY 
LAYER ON A YAWED FLAT PLATE. Harry 
Ashkenas and Frederick R. Rlddell, Cornell 
University. April 1955. 57p. diagrs., photos. 
(NACA TN 3383) 



ANALYTIC DETERMINATION OF THE DISCHARGE 
COEFFICIENTS OF FLOW NOZZLES. Frederick S. 
Simmons. April 1955. 15p. diagrs. (NACA 
TN 3447) 



COMPRESSIBLE FLOW 
(1.1.2) 



EFFECT OF WING SWEEP, TAPER, AND THICK- 
NESS RATIO ON THE TRANSONIC DRAG CHARAC- 
TERISTICS OF WING-BODY COMBINATIONS. Jim 
Rogers Thompson and Charles W. Mathews. 
December 31, 1948. 29p. diagrs., photos., 2 tabs. 
(NACA RM L8K01) 



INVESTIGATION OF SOME TURBULENT- 
BOUNDARY-LAYER VELOCITY PROFILES AT A 
TUNNEL WALL WITH MACH NUMBERS UP TO 1.2. 
Marshall P. Tulln and Ray H. Wr^ht. November 9, 
1949. 22p. diagrs. (NACA RM L9H29a) 



AERODYNAMICS 
2 FUNDAMENTAL (1. 1) 



Compressible Flow (Cont. ) 



AN 8-FOOT AXISYMMETRICAL FIXED NOZZLE 
FOR SUBSONIC MACH NUMBERS UP TO 0.99 AND 
FOR A SUPERSONIC MACH NUMBER OF 1.2. 
Virgil S. Ritchie, Ray H. Wright and Marshall P. 
Tulin. February 23, 1950. 52p. diagrs., photos., 
2 tabs. (NACA RM L50A03a) 

THE PATH AND MOTION OF SCALE MODELS OF 
JETTISONABLE NOSE SECTIONS AT SUPERSONIC 
SPEEDS AS DETERMINED FROM AN INVESTIGA- 
TION IN THE LANGLEY FREE -FLIGHT APPARA- 
TUS. Lawrence J. Gale. May 23, 1950. 35p. 
diagrs., photos., 2 tabs. (NACA RM L9J13a) 

SUMMARY OF RESULTS OBTAINED BY 
TRANSONIC-BUMP METHOD ON EFFECTS OF 
PLAN FORM AND THICKNESS OF LIFT AND DRAG 
CHARACTERISTICS OF WINGS AT TRANSONIC 
SPEEDS. Edward C. Polhamus. November 1951. 
33p. diagrs., tab. (NACA RM L51H30) 



FLUTTER INVESTIGATION OF TWO THIN, LOW- 
ASPECT-RATIO, SWEPT, SOLID, METAL WINGS 
IN THE TRANSONIC RANGE BY USE OF A FREE- 
FALLING BODY. W. T. Lauten, Jr. and Maurice 
A. Sylvester. February 1952. 12p. diagrs., photo., 

2 tabs. (NACA RM L51K28a) 

AN ANALYSIS OF BUZZING IN SUPERSONIC RAM 
JETS BY A MODIFIED ONE -DIMENSIONAL NON- 
STATIONAHY WAVE THEORY. Robert L. Trimpi. 
March 1952. 72p. diagrs., photos. (NACA 
RM L52A18) 

HEAT TRANSFER AND SKIN FRICTION FOR TUR- 
BULENT BOUNDARY LAYERS ON HEATED OR 
COOLED SURFACES AT HIGH SPEEDS. Coleman 
duP. Donaldson. October 1952. 20p. dlagr. , 

3 tabs. (NACA RM L52H04) 



DIRECT MEASUREMENTS OF SKIN FRICTION. 
Satish Dhawan, California Institute of Technology. 
1953. ii, 20p. diagrs., photos. (NACA Rept. 1121. 
Formerly TN 2567) 



EQUATIONS, TABLES, AND CHARTS FOR COM- 
PRESSIBLE FLOW. Ames Research Staff. 1953. 
iii, 69p. diagrs., 25 charts, 2 tabs. (NACA 
Rept. 1135. Formerly TN 1428) 



ON THE APPLICATION OF TRANSONIC SIMILARITY 
RULES TO WINGS OF FINITE SPAN. John R. 
Spreiter. 1953. il, 21p. diagrs. (NACA Rept. 1153. 
Formerly TN 2726) 

A COMPARISON OF THE EXPERIMENTAL SUB- 
SONIC PRESSURE DISTRIBUTIONS ABOUT SEV- 
ERAL BODIES OF REVOLUTION WITH PRESSURE 
DISTRIBUTIONS COMPUTED BY MEANS OF THE 
LINEARIZED THEORY. Clarence W. Matthews. 
1953. ii, 29p. diagrs., tab. (NACA Rept. 1155. 
Formerly TN 2519; RM L9F28) 

A THEORY FOR STABILITY AND BUZZ PULSATION 
AMPLITUDE IN RAM JETS AND AN EXPERIMEN- 
TAL INVESTIGATION INCLUDING SCALE EFFECTS. 
Robert L. Trimpi. October 1953. 75p. diagrs., 
photos., 3 tabs. (NACA RM L53G28) 



UNSTEADY OBLIQUE INTERACTION OF A SHOCK 
WAVE WITH A PLANE DISTURBANCE. Franklin K. 
Moore. 1954. ii, 21p. diagrs. (NACA Rept. 1165. 
Formerly TN 2879) 

SOME POSSIBILITIES OF USING GAS MIXTURES 
OTHER THAN AIR IN AERODYNAMIC RESEARCH. 
Dean R. Chapman. August 1954. 4Bp. diagrs., 4 
tabs. (NACA TN 3226) 

THE SMALL-DISTURBANCE METHOD FOR FLOW 
OF A COMPRESSIBLE FLUID WITH VELOCITY 
POTENTIAL AND STREAM FUNCTION AS INDE- 
PENDENT VARIABLES. Carl Kaplan. August lS54. 
18p. (NACA TN 3229) 

APPLICATION OF TWO-DIMENSIONAL VORTEX 
THEORY TO THE PREDICTION OF FLOW FIELDS 
BEHIND WINGS OF WING-BODY COMBINATIONS 
AT SUBSONIC AND SUPERSONIC SPEEDS. Arthur 
Wm. Rogers. September 1954. (ii), 91p. diagrs., 
photo., 3 tabs. (NACA TN 3227) 

SUBSONIC EDGES IN THIN-WING AND SLENDER- 
BODY THEORY. Milton D. Van Dyke. November 

1954. 26p. diagrs. (NACA TN 3343) 

ON THE SMALL-DISTURBANCE ITERATION 
METHOD FOR THE FLOW OF A COMPRESSIBLE 
FLUID WITH APPLICATION TO A PARABOLIC 
CYLINDER. Carl Kaplan. January 1955. 36p. 
diagrs., tab. (NACA TN 3318) 

SOME CONSIDERATIONS ON TWO-DIMENSIONAL 
THIN AIRFOILS DEFORMING IN SUPERSONIC 
FLOW. Eugene Migotsky. January 1955. 36p. 
diagrs. (NACA TN 3386) 

SIMILAR SOLUTIONS FOR THE COMPRESSIBLE 
LAMINAR BOUNDARY LAYER WITH HEAT 
TRANSFER AND PRESSURE GRADIENT. Clarence 
B. Cohen and Eli Reshotko. February 1955. 67p. 
diagrs., 2 tabs. (NACA TN 3325) 

A RAPID APPROXIMATE METHOD 'FOR THE 
DESIGN OF HUB SHROUD PROFILES OF CENTRIF- 
UGAL IMPELLERS OF GIVEN BLADE SHAPE. 
Kenneth J. Smith and Joseph T. Hamrick. March 

1955. 26p. diagrs., 3 tabs. (NACA TN 3399) 

THE COMPRESSIBLE LAMINAR BOUNDARY LAYER 
WITH FLUID INJECTION. George M. Low. March 
1955. 29p. diagrs., 3 tabs. (NACA TN 3404) 

THE COMPRESSIBLE LAMINAR BOUNDARYLAYER 
WITH HEAT TRANSFER AND ARBITRARY PRES- 
SURE GRADIENT. Clarence B. Cohen and Eli 
Reshotko. April 1955. 43p. diagrs., 2 tabs. (NACA 
TN 3326) 

A SELF-EXCITED, ALTERNATING-CURRENT, 
CONSTANT -TEMPERATURE HOT-WIRE ANEMOM- 
ETER. Charles E. Shepard. April 1955. 29p. 
diagrs., photos. (NACA TN 3406) 

ANALYTIC DETERMINATION OF THE DKCHARGE 
COEFFICIENTS OF FLOW NOZZLES. Frederick S. 
Simmons. April 1955. 15p. diagrs. (NACA 
TN 3447) 

SEPARATION, STABILITY, AND OTHER PROPER- 
TIES OF COMPRESSIBLE LAMINAR BOUNDARY 
LAYER WITH PRESSURE GRADIENT AND HEAT 
TRANSFER. Morris Morduchow and Richard G. 
Grape, Polytechnic Institute of Brooklyn. May 1955. 
45p. diagrs., 6 tabs. (NACA TN 3296) 



AERODYNAMICS 
FUNDAMENTAL, (1. 1) 



SUBSONIC FLOW 
(I. 1.2.1) 

ERROR IN AIRSPEED MEASUREMENT DUE TO 
STATIC -PRESSURE FIELD AHEAD OF SHARP- 
NOSE BODIES OF REVOLUTION AT TRANSONIC 
SPEEDS. Edward C. B. Danforth and J. Ford 
Johnston. August 19, 1949. 31p. diagrs., photos. 
(NACA RM L9C25) 

MEASUREMENTS OF THE DRAG AND PRESSURE 
DISTRIBUTION ON A BODY OF REVOLUTION 
THROUGHOUT TRANSITION FROM SUBSONIC TO 
SUPERSONIC SPEEDS. Jim Rogers Thompson. 
January 16, 1950. 36p. diagrs., photos., 2 tabs. 
(NACA RM L9J27) 

PRELIMINARY INVESTIGATION OF THE EFFECTS 
OF RECTANGULAR VORTEX GENERATORS ON 
THE PERFORMANCE OF A SHORT 1.9:1 
STRAIGHT -WALL ANNULAR DIFFUSER. Charles 
C. Wood. October 1951. 27p. diagrs., photo., tab. 
(NACARM L51G09) 

DIRECT MEASUREMENTS OF SKIN FRICTION. 
Satish Dhawan, California Institute of Technology. 
1953. ii, 20p. diagrs., photos. (NACA Rept. 1121. 
Formerly TN 2567) 

EQUATIONS, TABLES, AND CHARTS FOR COM- 
PRESSIBLE FLOW. Ames Research Staff. 1953. 
iii, 69p. diagrs., 25 charts, 2 tabs. (NACA 
Rept. 1135. Formerly TN 1428) 

ON TRANSONIC FLOW PAST A WAVE -SHAPED 
WALL. Carl Kaplan. 1953. ii, 12p. (NACA 
Rept. 1149. Formerly TN 2748) 

A COMPARISON OF THE EXPERIMENTAL SUB- 
SONIC PRESSURE DISTRIBUTIONS ABOUT SEV- 
ERAL BODIES OF REVOLUTION WITH PRESSURE 
DISTRIBUTIONS COMPUTED BY MEANS OF THE 
LINEARIZED THEORY. Clarence W. Matthews. 
1953. ii, 29p. diagrs., tab. (NACA Rept. 1155. 
Formerly TN 2519; RM L9F28) 

SECONDARY FLOWS AND BOUNDARY-LAYER 
ACCUMULATIONS IN TURBINE NOZZLES. Harold 
E. Rohlik, Milton G. Kofskey, Hubert W. Allen and 
Howard Z. Herzig. 1954. ii, 32p. diagrs., photos., 
3 tabs. (NACA Rept. 1168. Formerly TN 2871; 
TN 2909; TN 2989) 

METHOD FOR RAPID DETERMINATION OF PRES- 
SURE CHANGE FOR ONE -DIMENSIONAL FLOW 
WITH HEAT TRANSFER, FRICTION, ROTATION, 
AND AREA CHANGE. James E. Hubbartt, Henry O. 
Slone and Vernon L. Arne. June 1954. 22p. diagrs., 
2 tabs. (NACA TN 3150) 

SMOKE STUDY OF NOZZLE SECONDARY FLOWS 
IN A LOW-SPEED TURBINE. Milton G. Kofskey 
and Hubert W. Allen. November 1954. 24p. diagrs. , 
photos. (NACA TN 3260) 

APPROXIMATE EFFECT OF LEADING-EDGE 
THICKNESS, INCIDENCE ANGLE, AND INLET 
MACH NUMBER ON INLET LOSSES FOR HIGH- 
SOLIDITY CASCADES OF LOW CAMBERED 
BLADES. Linwood C. Wright. December 1954. 
38p. diagrs. (NACA TN 3327) 

PREDICTION OF LOSSES INDUCED BY ANGLES OF 
ATTACK IN CASCADES OF SHARP-NOSED BLADES 
FOR INCOMPRESSIBLE AND SUBSONIC COMPRES- 
SIBLE FLOW. James J. Kramer and John D. 
Stanitz. January 1955. 45p. diagrs. (NACA 
TN 3149) 



STUDY OF THE MOMENTUM DISTRIBUTION OF 
TURBULENT BOUNDARY LAYERS IN ADVERSE 
PRESSURE GRADIENTS. Virgil A. Sandborn and 
Raymond J. Slogar. January 1955. 79p. diagrs., 
photos. (NACA TN 3264) 

SECOND-ORDER SUBSONIC AIRFOIL -SECTION 
THEORY AND ITS PRACTICAL APPLICATION. 
Milton D. Van Dyke. March 1955. 50p. diagrs., 
5 tabs. (NACA TN 3390) 



AERODYNAMIC CHARACfERKTICS OF SEVERAL 
6-PERCENT -THICK AIRFOILS AT ANGLES OF 
ATTACK FROM 0° TO 2(P AT HIGH SUBSONIC 
SPEEDS. Bernard N. Daley and Douglas R. Lord. 
May 1955. 57p. diagrs., photos. (NACA TN 3424. 
Formerly RM L9E19) 



MIXED FLOW 
(1.1.2.2) 

DRAG OF A WING-BODY CONFIGURATION CON- 
SISTING OF A SWEPT-FORWARD TAPERED WING 
MOUNTED ON A BODY OF FINENESS RATIO 12 
MEASURED DURING FREE FALL AT TRANSONIC 
SPEEDS. Jim Rogers Thompson and Charles W. 
Mathews. March 13, 1947. 15p. diagrs., photos. 
(NACA RM L6L24) 

FLIGHT TESTS TO DETERMINE THE DRAG OF 
FIN -STABILIZED PARABOLIC BODIES AT TRAN- 
SONIC AND SUPERSONIC SPEEDS. Sidney R. 
Alexander, Leo T. Chauvln and Charles B. Rumsey. 
April 21, 1948. 24p. diagrs., photos. (NACA 
RM L8A05) 

APPLICATION OF ONE PART OF VON KARMAN'S 
TWO-DIMENSIONAL TRANSONIC SIMILARITY LAW 
TO DRAG DATA OF NACA 65-SERIES WINGS. • 
Kenneth B. Amer. August 24, 1948. 9p. diagrs. 
(NACA RM L8F24) 

EFFECT OF WING SWEEP, TAPER, ANii THICK- 
NESS RATIO ON THE TRANSONIC DRAG CHARAC- 
TERISTICS OF WING-BODY COMBINATIONS. Jim 
Rogers Thompson and Charles W. Mathews. 
December 31, 1948. 29p. diagrs., photos., 2 tabs. 
(NACA RM L8K01) 

ESTIMATION OF LIFT AND DRAG OF AIRFOILS AT 
NEAR SONIC SPEEDS AND IN THE PRESENCE OF 
DETACHED SHOCK WAVES. John P. Mayer. 
February 23, 1949. 23p. diagrs. (NACA RM L8L07) 

STUDY BY NACA WING-FLOW METHOD OF 
TRANSONIC DRAG CHARACTERISTICS OF A 
BLUNT-NOSE BODY OF REVOLUTION AND COM- 
PARISON WITH RESULTS FOR A SHARP-NOSE 
BODY. J. Ford Johnston and Mitchell Lopatoff. 
April 26, 1949. 26p. diagrs., photos. (NACA 
RM L9C11) 

ERROR IN AIRSPEED MEASUREMENT DUE TO 
STATIC-PRESSURE FIELD AHEAD OF SHARP- 
NOSE BODIES OF REVOLUTION AT TRANSONIC 
SPEEDS. Edward C. B. Danforth and J. Ford 
Johnston. August 19, 1949. 31p. diagrs., photos. 
(NACA RM L9C25) 



MEASUREMENTS OF THE DRAG AND PRESSURE 
DISTRIBUTION ON A BODY OF REVOLUTION 
THROUGHOUT TRANSITION FROM SUBSONIC TO 
SUPERSONIC SPEEDS. Jim Rogers Thompson. 
January 16, 1950. 36p. diagrs., photos., 2 tabs. 
(NACA RM L9J27) 



AERODYNAMICS 
4 FUNDAMENTAL, (1.1) 



Mixed Flow - Compressible (Cont. ) 



AN 8-FOOT AXISYMMETRICAL FIXED NOZZLE 
FOR SUBSONIC MACH NUMBERS UP TO 0.99 AND 
FOR A SUPERSONIC MACH NUMBER OF 1.2. 
Virgil S. Ritchie, Ray H. Wright and Marshall P. 
Tulin. February 23, 1950. 52p. diagrs., photos., 
2 tabs. (NACA RM L50A03a) 

PRESSURE MEASUREMENTS AT SUPERSONIC 
SPEEDS ON A SECTION OF A RECTANGULAR 
WING HAVING AN NACA 65-009 PROFILE. Robert 
W. Rainey. March 10, 1950. 31p. diagrs., photos,, 
tab. (NACA RM L9L16) 

PRELIMINARY INVESTIGATION OF THE TRAN- 
SONIC CHARACTERISTICS OF AN NACA SUB- 
MERGED INLET. John A. Axelson and Robert A. 
Taylor. June 5, 1950. 44p. diagrs., photos. 
(NA-CA RM A50C13) 

EXPERIMENTAL INVESTIGATION OF SUPERSONIC 
FLOW WITH DETACHED SHOCK WAVES FOR 
MACH NUMBERS BETWEEN 1.8 AND 2.9. W. E. 
Moeckel. July 5, 1950. 56p. diagrs., photos., 4 
tabs. (NACA RM E50D05) 

A PRELIMINAHY FLIGHT INVESTIGATION OF THE 
EFFECTS OF VORTEX GENERATORS ON SEPARA- 
TION DUE TO SHOCK. Lindsay J. Lina and Wilmer 
H. Reed, III. November 30, 1950. 30p. diagrs., 
photos., tab. (NACA RM L50J02) 

THE USE OF SUCTION TO PREVENT SHOCK- 
INDUCED SEPARATION IN A NOZZLE. James R. 
Sterrett, Robert W. Dunning and Maurice J. Brevoort. 
January 30, 1951. 64p. diagrs., photos., 2 tabs. 
(NACA RM L50K20) 

PRESSURE -DISTRIBUTION MEASUREMENTS OVER 
A 45° SWEPTBACK WING AT TRANSONIC SPEEDS 
BY THE NACA WING-FLOW METHOD. Edward 
C. B. Danforth and Thomas C. O'Bryan. June 1951. 
42p. diagrs., photos. (NACA RM L51D24) 

WING-FLOW STUDY OF PRESSURE-DRAG REDUC- 
TION AT TRANSONIC SPEED BY PROJECTING A 
JET OF AIR FROM THE NOSE OF A PROLATE 
SPHEROID OF FINENESS RATIO 6. Mitchell 
Lopatoff. October 1951. 20p. photos., diagrs., tab. 
(NACA RM L51E09) 

PRESSURE PULSATIONS ON RIGID AIRFOILS AT 
TRANSONIC SPEEDS. Milton D. Humphreys. 
December 1951. 21p. diagrs., photos., tab. 
(NACARM L51I12) 

A CORRELATION BY MEANS OF THE TRANSONIC 
SIMILARITY RULES OF THE EXPERIMENTALLY 
DETERMINED CHARACTERISTICS OF 22 RECTAN- 
GULAR WINGS OF SYMMETRICAL PROFILE. 
John B. McDevitt. February 1952. 60p. diagrs., 
3 tabs. (NACA RM A51L17b) 

THE EFFECTS OF CAMBER AND LEADING-EDGE- 
FLAP DEFLECTION ON THE PRESSURE PULSA- 
TIONS ON THIN RIGID AIRFOH.S AT TRANSONIC 
SPEEDS. Milton D. Humphreys and John D. Kent. 
October 1952. 26p. diagrs., photos., tab. (NACA 
RM L52G22) 

EFFECT OF THICKNESS, CAMBER, AND THICK- 
NESS DKTRIBUTION ON AIRFOIL CHARACTERIS- 
TICS AT MACH NUMBERS UP TO 1.0. Bernard N. 
Daley and Richard S. Dick. October 1952. 76p. 
photos., diagrs., tab. (NACA RM L52G31a) 



THE EFFECTS OF A SMALL JET OF AIR EX- 
HAUSTING FROM THE NOSE OF A BODY OF REV- 
OLUTION IN SUPERSONIC FLOW. Eugene S. Love. 
November 1952. 45p. diagrs., photos. (NACA 
RM L52I19a) 

ON TRANSONIC FLOW PAST A WAVE -SHAPED 
WALL. Carl Kaplan. 1953. ii, 12p. (NACA 
Rept. 1149. Formerly TN 2748) 



A COMPARISON OF THE EXPERIMENTAL SUB- 
SONIC PRESSURE DISTRIBUTIONS ABOUT SEV- 
ERAL BODIES OF REVOLUTION WITH PRESSURE 
DISTRIBUTIONS COMPUTED BY MEANS OF THE 
LINEARIZED THEORY. Clarence W. Matthews. 
1953. ii, 29p. diagrs., tab. (NACA Rept. 1155. 
Formerly TN 2519; RM L9F28) 

A CORRELATION BY MEANS OF TRANSONIC 
SIMILARITY RULES OF THE EXPERIMENTALLY 
DETERMINED CHARACTERISTICS OF 18 CAM- 
BERED WINGS OF RECTANGULAR PLAN FORM. 
John B. McDevitt. September 1953. 57p. diagrs. 
(NACARM A53G31) 

TRANSONIC AERODYNAMIC CHARACTERISTICS 
OF AN NACA 64A006 AIRFOIL SECTION WITH A 
15-PERCENT -CHORD LEADING-EDGE FLAP. 
Milton D. Humphreys. September 1953. 44p. 
diagrs., photos. (NACA RM L53G23) 

THEORETICAL STUDY OF THE TRANSONIC LIFT 
OF A DOUBLE -WEDGE PROFILE WITH DETACHED 
BOW WAVE. Walter G. Vincenti and Cleo B. 
Wagoner. (Portions of this work were reported at 
the eighth International Congress on Theoretical and 
Applied Mechanics, Istanbul, Turkey, August 20-28, 
1952). 1954. 11, 24p. diagrs., 2 tabs. (NACA 
Rept. 1180. Formerly TN 2832) 

AN EXPERIMENTAL STUDY OF THE LIFT AND 
PRESSURE DISTRIBUTION ON A DOUBLE -WEDGE 
PROFILE AT MACH NUMBERS NEAR SHOCK 
ATTACHMENT. Walter G. Vincenti^ Duane W. Dugan 
and E. Ray Phelps. July 1954. 43p. diagrs. 
(NACA TN 3225) 

TRANSONIC FLOW PAST CONE CYLINDERS. 
George E. Solomon, California Institute of Technology. 
September 1954. 56p. diagrs., photos. (NACA 
TN 3213) 

AN INVESTIGATION OF A LIFTING 10-PERCENT- 
THICK SYMMETRICAL DOUBLE-WEDGE AIRFOIL 
AT MACH NUMBERS UP TO 1. Milton D. 
Humphreys. November 195^. 35p. diagrs., photos., 
tab. (NACA TN 3306) 

AERODYNAMIC CHARACTERISTICS OF SEVERAL 
6-PERCENT -THICK AIRFOILS AT ANGLES OF 
ATTACK FROM 0° TO 20° AT HIGH SUBSONIC 
SPEEDS.' Bernard N. Daley and Douglas R. Lord. 
May 1955. 57p. diagrs., photos. (NACA TN 3424. 
Formerly RM L9E19) 



SUPERSONIC FLOW 
(1.1.2. 3) 



FLIGHT TESTS TO DETERMINE THE DRAG OF 
FIN-STABILIZED PARABOLIC BODIES AT TRAN- 
SONIC AND SUPERSONIC SPEEDS. Sidney R. 
Alexander, Leo T. Chairsin and Charles B. Rumsey, 
April 21, 1948. 24p. diagrs., photos. (NACA 
RM L8A05) 



AERODYNAMICS 
FUNDAMENTAL (1. 1) 



Supersonic Flow 
(Cont. ) 



Compressible 



EFFECT OF WING SWEEP, TAPER, AND THICK- 
NESS RATIO ON THE TRANSONIC DRAG CHARAC- 
TERISTICS OF WING-BODY COMBINATIONS. Jim 
Rogers Thompson and Charles W. Mathews. 
December 31, 1948. 29p. diagrs., photos., 2 tabs. 
(NACA RM L8K01) 

EXPERIMENTAL PRESSURE DISTRIBUTIONS OVER 
WING TIPS AT MACH NUMBER 1.9. I - WING TIP 
WITH SUBSONIC LEADING EDGE. James M. 
Jagger and Harold Mirels. January 27, 1949. 28p. 
diagrs. photo. (NACA RM E8K26) 

ESTIMATION OF LIFT AND DRAG OF AIRFOILS AT 
NEAR SONIC SPEEDS AND IN THE PRESENCE OF 
DETACHED SHOCK WAVES. John P. Mayer. 
February 23, 1949. 23p. diagrs. (NACA RM L8L07) 

STUDY BY NACA WING-FLOW METHOD OF 
TRANSONIC DRAG CHARACTERISTICS OF A 
BLUNT-NOSE BODY OF REVOLUTION AND COM- 
PARISON WITH RESULTS FOR A SHARP-NOSE 
BODY. J. Ford Johnston and Mitchell Lopatoff. 
April 26, 1949. 26p. diagrs., photos. (NACA 
RM L9C11) 

TESTS OF LIFTING SURFACES ON CONICAL AND 
CYLINDRICAL PORTIONS OF A BODY AT SUBSONIC 
MACH NUMBERS AND AT A MACH NUMBER OF 1.2. 
Robert S. Osborne and John B. Wright. September 2, 
1949. 22p. diagrs. (NACA RM L9F29) 

EXPERIMENTAL PRESSURE DISTRIBUTIONS OVER 
WING TIPS AT MACH NUMBER 1.9. II - WING TIP 
WITH SUBSONIC TRAILING EDGE. Harold Mirels 
and James M. Jagger. December 21, 1949. 23p. 
diagrs., photo. (NACA RM E9I22a) 

MEASUREMENTS OF THE DRAG AND PRESSURE 
DISTRIBUTION ON A BODY OF REVOLUTION 
THROUGHOUT TRANSITION FROM SUBSONIC TO 
SUPERSONIC SPEEDS. Jim Rogers Thompson. 
January 16, 1950. 36p. diagrs., photos., 2 tabs. 
(NACA RM L9J27) 

INVESTIGATION AT MACH NUMBER 1.62 OF THE 
PRESSURE DISTRIBUTION OVER A RECTANGULAR 
WING WITH SYMMETRICAL CIRCULAR -ARC SEC- 
TION AND 30-PERCENT-CHORD TRAILING-EDGE 
FLAP. K. R. Czarnecki and James N. Mueller. 
January 25, 1950. 81p. diagrs., photos. (NACA 
RM L9J05) 

THE TIME LAG BETWEEN FLAP DEFLECTION 
AND FORCE DEVELOPMENT AT A MACH NUMBER 
OF 4. Walter F. Lindsey and Edward F. Ulmann. 
February 13, 1950. lip. diagr., photos. (NACA 
RM L9L15) 

AN 8-FOOT AXISYMMETRICAL FIXED NOZZLE 
FOR SUBSONIC MACH NUMBERS UP TO 0.99 AND 
FOR A SUPERSONIC MACH NUMBER OF 1.2. 
Virgil S. Ritchie, Ray H. Wright and Marshall P. 
Tulln. February 23, 1950. 52p. diagrs., photos., 
2 tabs. (NACA RM L50A03a) 

AERODYNAMIC INVESTIGATION AT MACH NUM- 
BER 1.92 OF A RFCTANGtra^AR WING AND TAIL 
AND BODY CONFIGURATION AND ITS COMPO- 
NENTS. Macon C. Ellis, Jr. and Carl E. Grigsby. 
March 1, 1950. 96p. diagrs., photos., 4 tabs. 
(NACA RM L9L28a) 



PRESSURE MEASUREMENTS AT SUPERSONIC 
SPEEDS ON A SECTION OF A RECTANGULAR 
WING HAVING AN NACA 65-009 PROFILE. Robert 
W. Rainey. March 10, 1950. 31p. diagrs., photos., 
tab. (NACA RM L9L16) 

EXPERIMENTAL INVESTIGATION OF SUPERSONIC 
FLOW WITH DETACHED SHOCK WAVES FOR 
MACH NUMBERS BETWEEN 1.8 AND 2.9. W. E. 
Moeckel. July 5, 1950. 56p. diagrs., photos., 4 
tabs. (NACA RM E50D05) 

DOWNWASH IN VORTEX REGION BEHIND RECTAN- 
GULAR HALF-WING AT MACH NUMBER 1.91. John 
L. Cummlngs and Rttdolph C. Haefell. October 26, 
1950. 43p. diagrs., photos., tab. (NACA 
RM E50H10) 

THE EXTERNAL-SHOCK DRAG OF SUPERSONIC 
INLETS HAVING SUBSONIC ENTRANCE FLOW. 
Louis M. Nucci. December 20, 1950. 28p. diagrs., 
photos. (NACA RM L50G14a) 



INVESTIGATION AT SUPERSONIC SPEEDS OF SOME 
OF THE FACTORS AFFECTING THE FLOW OVER A 
RECTANGULAR WING WITH SYMMETRICAL 
CIRCULAR-ARC SECTION AND 30-PERCENT- 
CHORD TRAILING-EDGE FLAP. K. R. Czarnecki 
and James N. Mueller. January 2, 1951. lllp. 
diagrs., photos. (NACA RM L50J18) 

SUPERSONIC TUNNEL INVESTIGATION BY MEANS 
OF INCLINED-PLATE TECHNIQUE TO DETERMINE 
PERFORMANCE OF SEVERAL NOSE INLETS OVER 
MACH NUMBER RANGE OF 1.72 TO 2.18. Jerome 
L. Fox. February 14, 1951. 27p. diagrs., photos. 
(NACA RM E50K14) 

VELOCITY AND TEMPERATURE FIELDS IN CIR- 
CULAR JET EXPANDING FROM CHOKED NOZZLE 
INTO QUIESCENT AIR. Morris D. Rousso and 
Fred D. Kochendorfer. July 1951. 34p. diagrs., 
photos. (NACA RM E51F18. Formerly 
RM E50E03a) 

APPARATUS FOR OBTAINING A SUPERSONIC 
FLOW OF VERY SHORT DURATION AND SOME 
DRAG MEASUREMENTS OBTAINED WITH ITS USE. 
John E. Yeates, Jr. , F. J. Bailey, Jr. and T. J. 
Voglewede. July 23, 1951. 23p. diagrs., photos. 
(NACA RM L9C01) 

WING-FLOW STUDY OF PRESSURE-DRAG REDUC- 
TION AT TRANSONIC SPEED BY PROJECTING A 
JET OF AIR FROM THE NOSE OF A PROLATE 
SPHEROID OF FINENESS RATIO 6. Mitchell 
Lopatoff. October 1951. 20p. photosi, diagrs., tab. 
(NACA RM L51E09) 

BODIES OF REVOLUTION FOR MINIMUM DRAG AT 
HIGH SUPERSONIC AIRSPEEDS. A. J. Eggers, Jr., 
David H. Dennis and Meyer M. Resnikoff. February 
1952. 44p. diagrs., photos. (NACA RM A51K27) 

PRESSURE DISTRIBUTION AND AERODYNAMIC 
COEFFICIENTS ASSOCIATED WITH HEAT ADDI- 
TION TO SUPERSONIC AIR STREAM ADJACENT TO 
TWO-DIMENSIONAL SUPERSONIC WING. I. Irving 
Pinkel, John S. Serafini and John L. Gregg. February 
1952. 33p. diagrs., tab. (NACA RM E51K26) 

THE EFFECT OF BLUNTNESS ON THE DRAG OF 
SPHERICAL-TIPPED TRUNCATED CONES OF 
FINENESS RATIO 3 AT MACH NUMBERS 1.2 TO 
7.4. Simon C. Sommer and James A. Stark. April 
1952. 18p. photos., diagrs. (NACA RM A52B13) 



AERODYNAMICS 
FUNDAMENTAL (1. 



1) 



Supersonic Flow - Compressible 
(Cont. ) 

PRELIMINARY INVESTIGATION OF THE DRAG 
CHARACTERISTICS OF THE NACA RM-10 MISSILE 
AT MACH NUMBERS OF 1.40 AND 1.59 IN THE 
LANGLEY 4- BY 4-FOOT SUPERSONIC TUNNEL. 
Lowell E. Hasel, Archibald R. Sinclair and Clyde V. 
Hamilton, April 1952. 49p. diagrs., photos, 3 tabs. 
(NACA RM L52A14) 

FLIGHT MEASUREMENTS OF THE EFFECTS OF 
SURFACE CONDITION ON THE SUPERSONIC DRAG 
OF FIN-STABILIZED PARABOLIC BODIES OF REV- 
OLUTION. H. Herbert Jackson. May 1952. 17p. 
diagrs., photos. (NACA RM L52B26) 

SUPPLEMENTARY NOTE ON MODIFIED -IMPACT - 
THEORY CALCULATIONS FOR BODIES OF REVO- 
LUTION HATTOIG MINIMUM DRAG AT HYPERSONIC 
SPEEDS. Meyer M. Resnikoff. July 1952. 13p. 
diagr. (NACA RM A52D24) 

EFFECTS OF PLAN FORM, AIRFOIL SECTION, 
AND ANGLE OF ATTACK ON THE PRESSURES 
ALONG THE BASE OF BLUNT -TRAILING-EDGE 
WINGS AT MACH NUMBERS OF 1.41, 1.62, AND 
1.96. Kennith L. Goin. September 1952. 52p. 
photos., diagrs. (NACA RM L52D21) 

INVESTIGATION OF THE VARIATION WITH 
REYNOLDS NUMBER OF THE BASE, WAVE, AND 
SKIN-FRICTION DRAG OF A PARABOLIC BODY OF 
REVOLUTION (NACA RM-10) AT MACH NUMBERS 
OF 1.62, 1.93, AND 2.41 IN THE LANGLEY 9-INCH 
SUPERSONIC TUNNEL. Eugene S. Love, Donald E. 
Coletti and August F. Bromm, Jr. October 1952. 
62p. diagrs., photos., (NACA RM L52K21) 

THE EFFECTS OF A SMALL JET OF AIR EX- 
HAUSTING FROM THE NOSE OF A BODY OF REV- 
OLUTION IN SUPERSONIC FLOW. Eugene S. Love. 
November 1952. 45p. diagrs., photos. (NACA 
RM L52I19a) 

EQUATIONS, TABLES, AND CHARTS FOR COM- 
PRESSIBLE FLOW. Ames Research Staff. 1953. 
iii, 69p. diagrs., 25 charts, 2 tabs. (NACA 
Rept. 1135. Formerly TN 1428) 

A VECTOR STUDY OF LINEARIZED SUPERSONIC 
FLOW APPLICATIONS TO NONPLANAR 
PROBLEMS. John C. Martin. 1953. ii, 34p. 
diagrs., tab. (NACA Rept. 1143. Formerly 
TN 2641) 

THE ZERO-LIFT DRAG OF A SLENDER BODY OF 
REVOLUTION (NACA RM-10 RESEARCH MODEL) 
AS DETERMINED FROM TESTS IN SEVERAL WIND 
TUNNELS AND IN FLIGHT AT SUPERSONIC 
SPEEDS. Albert J. Evans. 1954. ii, 13p. 
diagrs., tab. (NACA Rept. 1160. Formerly 
TN 2944) 

CONVECTION OF A PATTERN OF VORTICITY 
THROUGH A SHOCK WAVE. H. S. Rlbner. 1954. 
ii, 17p. diagrs. (NACA Rept. 1164. Formerly 
TN 2864) 

SECONDARY FLOWS AND BOUNDARY-LAYER 
ACCUMULATIONS IN TURBINE NOZZLES. Harold 
E. Rohlik, Milton G. Kofskey, Hubert W. Allen and 
Howard Z. Herzig. 1954. ii, 32p. diagrs., photos., 
3 tabs. (NACA Rept. 1168. Formerly TN 2871; 
TN 2909; TN 2989) 

SOME NEW DRAG DATA ON THE NACA RM-10 
MISSILE AND A CORRELATION OF THE EXISTING 
DRAG MEASUREMENTS AT M = 1.6 AND 3.0. 
Robert J. Carros and Carlton S. James. June 1954. 
24p. diagrs., photos., tab. (NACA TN 3171) 



TABLES FOR THE COMPUTATION OF WAVE DRAG 
OF ARROW WINGS OF ARBITRARY AIRFOIL SEC- 
TION. Frederick C. Grant and Morton Cooper. 
June 1954. 9p. diagr., 28p. tabs, (in pocket) (NACA 
TN 3185) 

AN EXPLORATORY INVESTIGATION OF SKIN 
FRICTION AND TRANSITION ON THREE BODIES 
OF REVOLUTION AT A MACH NUMBER OF 1.61. 
John H. Hilton, Jr. and K. R. Czarnecki. June 
1954. 15p. diagrs. (NACA TN 3193) 

MEASUREMENT OF HEAT TRANSFER IN THE TUR- 
BULENT BOUNDARY LAYER ON A FLAT PLATE 
IN SUPERSONIC FLOW AND COMPARISON WITH 
SKIN- FRICTION RESULTS. C. C. Pappas. June 
1954. 32p. diagrs., tab. (NACA TN 3222) 

LIFT AND PITCHING MOMENT AT SUPERSONIC 
SPEEDS DUE TO CONSTANT VERTICAL ACCELER- 
ATION FOR THIN SWEPTBACK TAPERED WINGS 
WITH STREAMWISE TIPS. SUPERSONIC LEADING 
AND TRAILING EDGES. Isabella J. Cole and 
Kenneth Margolis. July 1954. 67p. diagrs., 4 tabs. 
(NACA TN 3196) 

SHOCK-TURBULENCE INTERACTION AND THE 
GENERATION OF NOISE. H. S. Rlbner. July 1954. 
60p. diagrs., tab. (NACA TN 3255) 

AN ANALYSIS OF SHOCK-WAVE CANCELLATION 
AND REFLECTION FOR POROUS WALLS WHICH 
OBEY AN EXPONENTIAL MASS-FLOW PRESSURE-- 
DIFFERENCE RELATION. Joseph M. Spiegel and 
Phillips J. Tunnell. August 1954. 23p. diagrs. 
(NACA TN 3223) 

INVESTIGATION OF MACH NUMBER CHANGES 
OBTAINED BY DISCHARGING HIGH -PRESSURE 
PULSE THROUGH WIND TUNNEL OPERATING 
SUPERSONICALLY. Rudolph C. Haefeli and Harry 
Bernstein. August 1954. 14p. diagrs., photos., 
tab. (NACA TN 3258) 

EXAMINATION OF THE EXISTING DATA ON THE 
HEAT TRANSFER OF TURBULENT BOUNDARY 
LAYERS AT SUPERSONIC SPEEDS FROM THE 
POINT OF VIEW OF REYNOLDS ANALOGY. Alvin 
Seiff. August 1954. 38p. diagrs., tab. (NACA 
TN 3284) 

HEAT TRANSFER FROM A HEMISPHERE- 
CYUNDER EQUIPPED WITH FLOW -SEPARATION 
SPIKES. Jackson R. Stalder and Helmer V. Nielsen. 
September 1954. 29p. diagrs., photos. (NACA 
TN 3287) 

INVESTIGATION OF LIFT, DRAG, AND PITCHING 
MOMENT OF A 60° DELTA-WING— BODY COM- 
BINATION (AGARD CALIBRATION MODEL B) IN 
THE LANGLEY 9-INCH SUPERSONIC TUNNEL 
August F. Bromm, Jr. September 1954. 18p. 
diagrs., photos. (NACA TN 3300) 

TURBULENT-HEAT -TRANSFER MEASUREMENTS 
AT A MACH NUMBER OF 3.03. Maurice J. 
Brevoort and Bernard Rashis. September 1954. 
21p. diagrs., tab. (NACA TN 3303) 

LIQUEFACTION OF AIR IN THE LANGLEY 11 -INCH 
HYPERSONIC TUNNEL. Charles H. McLellan and 
Thomas W. Williams. October 1954. 36p. diagrs., 
4 tabs. (NACA TN 3302) 

EXPERIMENTAL DETERMINATION OF BOUNDARY- 
LAYER TRANSITION ON A. BODY OF REVOLUTION 
AT M = 3.5. James R. Jedlicka, Max E. Wilkins 
and Alvin Seiff. October 1954. 56p. diagrs., photos. 
(NACA TN 3342. Formerly RM A53L18) 



AERODYNAMICS 
FUNDAMENTAL (1.1) 



Supersonic Flow 
(Cont. ) 



Compressi6le 



ON THE DETERMINATION OF CERTAIN BASIC 
TYPES OF SUPERSONIC FLOW FIELDS. (Sulla 
determinazione dl alcuni tlpl di campi di corrente 
Ipersonora). Carlo Ferrari. November 1954. 17p. 
diagrs. (NACA TM 1381. Trans, from Rendiconti 
della R. Accademie Nazionale del Llncei, Series 8, 
V.7, no. 6, Dec. 1949) 

VISCOSITY CORRECTIONS TO CONE PROBES IN 
RAREFIED SUPERSONIC FLOW AT A NOMINAL 
MACH NUMBER OF 4. L. Talbot, University of 
California. November 1954. 39p. diagrs., photo., 

4 tabs. (NACA TN 3219) 

INITIAL EXPERIMENTS ON FLUTTER OF UN- 
SWEPT CANTILEVER WINGS AT MACH NUMBER 
1..3. W. J. Tuovila, John E. Baker and Arthur A. 
Regier. November 1954. 19p. diagrs., photos., 
2 tabs. (NACA TN 3312. Formerly RM L8J11) 

ARRANGEMENT OF FUSIFORM BODIES TO RE- 
DUCE THE WAVE DRAG AT SUPERSONIC SPEEDS. 
Morris D. Friedman and Doris Cohen. November 
1954 23p. diagrs. (NACA TN 3345. Formerly 
RM A51I20) 

THEORETICAL CALCULATIONS OF THE LATERAL 
STABILITY DERIVATIVES FOR TRIANGULAR VER- 
TICAL TAILS WITH SUBSONIC LEADING EDGES 
TRAVELING AT SUPERSONIC SPEEDS. Percy J. 
Bobbitt. December 1954, 68p. diagrs., photos., 

5 tabs. (NACA TN 3240) 

BOUNDARY-LAYER TRANSITION AT MACH 3.12 
WITH AND WITHOUT SINGLE ROUGHNESS 
ELEMENTS. Paul F. Brinich. December 1954. 
41 p. diagrs. (NACA TN 3267) 

SHOCKS IN HELICAL FLOWS THROUGH ANNULAR 
CASCADES OF STATOR BLADES. Robert 
Wasserman and Arthur W. Goldstein. December 
1954. 27p. diagrs. (NACA TN 3329) 

GENERAL THEORY OF CONICAL FLOWS AND ITS 
APPLICATION TO SUPERSONIC AERODYNAMICS. 
(La theorie generate des mouvements coniques et 
ses applications a I'aerodynamique supersonique). 
Paul Germain. PREFACE. M. J. Peres. 
January 1955. vii, 333p. diagrs. (NACA 
TM 1354. Trans, from Office National d'itudes et 
de Recherches Aeronautiques, Pub. 34, 1949) 

AN ACCURATE AND RAPID METHOD FOR THE 
DESIGN OF SUPERSONIC NOZZLES. Ivan E. 
Beckwith and John A. Moore. February 1955. 
57p. diagrs., 3 tabs. (NACA TN 3322) 

MINIMUM -DRAG BODIES OF REVOLUTION IN A 
NONUNIFORM SUPERSONIC FLOW FIELD. Conrad 
Rennemann, Jr. Febrxiary 1955. 25p. diagrs. 
(NACA TN 3369) 

National Advisory Committee for Aeronautics. 
AXIALLY SYMMETRIC SHAPES WITH MINIMUM 
WAVE DRAG. Max. A. Heaslet and Franklyn B. 
Fuller. Ffebruary 1955. 46p. diagrs. (NACA 
TN 3389) 

THEORETICAL CALCULATIONS OF THE PRES- 
SURES, FORCES, AND MOMENTS DUE TO 
VARIOUS LATERAL MOTIONS ACTING ON THIN 
ISOLATED VERTICAL TAILS WITH SUPERSONIC 
LEADING AND TRAILING EDGES. Kenneth 
Margolis. March 1955. 43p. diagrs., 10 tabs. 
(NACA TN 3373) 



TURBULENT -HEAT-TRANSFER MEASUREMENTS 
AT A MACH NUMBER OF 2.06. Maurice J. 
Brevoort and Bernard Rashis. March 1955. 20p. 
diagrs., tab. (NACA TN 3374) 

FREE -FLIGHT MEASUREMENTS OF TURBULENT- 
BOUNDARY- LAYER SKIN FRICTION IN THE PRE- 
SENCE OF SEVERE AERODYNAMIC HEATING AT 
MACH NUMBERS FROM 2.8 TO 7.0. Simon C. 
Sommer and Barbara J. Short. March 1955. 47p. 
diagrs.. photos., 2 tabs. (NACA TN 3391) 

AN EXPERIMENTAL INVESTIGATION OF THE 
BASE PRESSURE CHARACTERISTICS OF NON- 
LIFTING BODIES OF REVOLUTION AT MACH 
NUMBERS FROM 2.73 TO 4.98. John O. Reller, Jr. 
and Frank M. Hamaker. March 1955. 45p. diagrs., 
photos. (NACA TN 3393. Formerly RM A52E20) 

APPLICATION OF THE GENERALIZED SHOCK- 
EXPANSION METHOD TO INCLINED BODIES OF 
REVOLUTION TRAVELING AT HIGH SUPERSONIC 
AIRSPEEDS. Raymond C. Savin. April 1955. 
71p. diagrs., photos., tab. (NACA TN 3349) 

THE ZERO-LIFT WAVE DRAG OF A PARTICULAR 
FAMILY OF UNSWEPT, TAPERED WINGS WITH 
LINEARLY VARYING THICKNESS RATIO. Arthur 
Henderson, Jr. and Julia M. Goodwin. May 1955. 
28p. diagrs. (NACA TN 3418) 

EFFECT OF A DISCONTINUITY ON TURBULENT 
BOUNDARY-LAYER-THICKNESS PARAMETERS 
WITH APPLICATION TO SHOCK-INDUCED SEPARA- 
TION. Eli Reshotko and Maurice Tucker. May 1955. 
21p. diagrs. (NACA TN 3454) 



VISCOUS FLOW 
(1.1.3) 



INVESTIGATION OF SOME TURBULENT- 
BOUNDARY-LAYER VELOCITY PROFILES AT A 
TUNNEL WALL WITH MACH NUMBERS UP TO 1.2. 
Marshall P. Tulln and Ray H. Wright. November 9, 
1949. 22p. diagrs. (NACA RM L9H29a) 

INVESTIGATION AT MACH NUMBER 1.62 OF THE 
PRESSURE DISTRIBUTION OVER A RECTANGULAR 
WING WITH SYMMETRICAL CIRCULAR-ARC SEC- 
TION AND 30-PERCENT -CHORD TRAILING-EDGE 
FLAP. K. R. Czarnecki and James N. Mueller. 
January 25, 1950. 81p. diagrs., photos. (NACA 
RM L9J05) 

PRELIMINARY INVESTIGATION OF THE DELAY 
OF TURBULENT FLOW SEPARATION BY MEANS 
OF WEDGE-SHAPED BODIES. George B. 
McCuUough, Gerald E. Nitzberg and John A. Kelly. 
March 1, 1951. 28p. diagrs., photos. (NACA 
RM A50L12) 

A SEMIEMPIRICAL METHOD FOR CALCULATING 
THE PITCHING MOMENT OF BODIES OF REVO- 
LUTION AT LOW MACH NUMBERS. Edward J. 
Hopkins. May 17, 1951. 27p. diagrs., tab. (NACA 
RM A51C14) 

A SUMMARY OF AVAILABLE KNOWLEDGE CON- 
CERNING SKIN FRICTION AND HEAT TRANSFER 
AND ITS APPLICATION TO THE DESIGN OF HIGH- 
SPEED MISSILES. Morris W. Rubesin, Charles B. 
Rumsey and Steven A. Varga. November 1951. 17p. 
diagrs. (NACA RM A51J25a) 



AERODYNAMICS 
FUNDAMENTAL (1. 



1) 



Viscous Flow (Cont. ) 

EXPERIMENTAL INVESTIGATION OF THE EF- 
FECTS OF VORTEX GENERATORS ON THE MAXI- 
MUM LIFT OF A 6-PERCENT -THICK SYMMETRI- 
CAL CIRCULAR-ARC AIRFOIL SECTION. William 
J. Bursnall. October 1952. 16p. diagrs., 2 tabs. 
(NACA RM L52G24) 

DIRECT MEASUREMENTS OF SKIN FRICTION. 
Satish Dhawan, California Institute of Technology. 
1953. 11, 20p. diagrs., photos. (NACA Rept. 1121. 
Formerly TN 2567) 

A VISUALIZATION STUDY OF SECONDARY FLOWS 
IN CASCADES. Howard Z. Herzig, Arthur G. 
Hansen and George R. Costello. 1954. ii, 51p. 
diagrs., photos. (NACA Rept. 1163. Formerly 
TN 2947; RM E52F19) 

EXPERIMENTAL INVESTIGATION OF TEMPERA- 
TURE RECOVERY FACTORS ON A 10° CONE AT 
ANGLE OF ATTACK AT A MACH NUMBER OF 3.12. 
John R. Jack and Barry Moskowitz. July 1954. 15p. 
diagrs. (NACA TN 3256) 

VISCOSITY CORRECTIONS TO CONE PROBES IN 
RAREFIED SUPERSONIC FLOW AT A NOMINAL 
MACH NUMBER OF 4. L. Talbot, University of 
California. November 1954. 39p. diagrs., photo., 
4 tabs. (NACA TN 3219) 

SMOKE STUDY OF NOZZLE SECONDARY FLOWS 
IN A LOW-SPEED TURBINE. Milton G. Kofskey 
and Hubert W. Allen. November 1954. 24p. diagrs. , 
photos. (NACA TN 3260) 

SHEARING-STRESS MEASUREMENTS BY USE OF A 
HEATED ELEMENT. H. W. Liepmann and G. T. 
Skinner, California Institute of Technology. 
November 1954. 27p. diagrs. (NACA TN 3268) 

THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF AERODYNAMIC -HEATING AND ISOTHER- 
MAL HEAT -TRANSFER PARAMETERS ON A 
HEMISPHERICAL NOSE WITH LAMINAR BOUNDARY 
LAYER AT SUPERSONIC MACH NUMBERS. 
Howard A. Stine and Kent Wanlass. December 1954. 
48p. diagrs., photo., tab. (NACA TN 3344) 

A FIBROUS-GLASS COMPACT AS A PERMEABLE 
MATERIAL FOR BOUNDARY-LAYER-CONTROL 
APPLICATIONS USING AREA SUCTION. Robert E. 
Dannenberg, James A. Weiberg and Bruno J. 
Gambucci. January 1955. 20p. diagrs., photos., 
2 tabs. (NACA TN 3388) 

A THEORY FOR PREDICTING THE FLOW OF REAL 
GASES IN SHOCK TUBES WITH EXPERIMENTAL 
VERIFICATION. Robert L. Trimpi and Nathaniel B. 
Cohen. March 1955. 69p. diagrs., photo. 
(NACA TN 3375) 

AN EXPERIMENTAL INVESTIGATION OF THE 
BASE PRESSURE CHARACTERISTICS OF NON- 
LIFTING BODIES OF REVOLUTION AT MACH 
NUMBERS FROM 2.73 TO 4.98. John O. Reller, Jr. 
and Frank M. Hamaker. March 1955. 45p. diagrs., 
photos. (NACA TN 3393. Formerly RM A52E20) 



LAMINAR FLOW 
(1. 1.3. 1) 

PRESSURE MEASUREMENTS AT SUPERSONIC 
SPEEDS ON A SECTION OF A RECTANGULAR 
WING HAVING AN NACA 65-009 PROFILE. Robert 
W. Rainey. March 10, 1950. 31p. diagrs., photos., 
tab. (NACA RM L9L16) 



INVESTIGATION AT SUPERSONIC SPEEDS OF SOME 
OF THE FACTORS AFFECTING THE FLOW OVER A 
RECTANGULAR WING WITH SYMMETRICAL 
CIRCULAR-ARC SECTION AND 30-PERCENT- 
CHORD TRAILING-EDGE FLAP. K. R. Czarnecki 
and James N. Mueller. January 2, 1951. lllp. 
diagrs., photos. (NACA RM L50J18) 

PRELIMINARY INVESTIGATION OF THE DRAG 
CHARACTERISTICS OF THE NACA RM-10 MISSILE 
AT MACH NUMBERS OF 1.40 AND 1.59 IN THE 
LANGLEY 4- BY 4-FOOT SUPERSONIC TUNNEL. 
Lowell E. Hasel, Archibald R. Sinclair and Clyde V. 
Hamilton, April 1952. 49p. diagrs., photos, 3 tabs. 
(NACA RM L52A14) 

SKIN-FRICTION DRAG AND BOUNDARY- LAYER 
TRANSITION ON A PARABOLIC BODY OF REVO - 
LUTION (NACA RM-10) AT A MACH NUMBER OF 
1.6 IN THE LANGLEY 4- BY 4-FOOT SUPERSONIC 
PRESSURE TUNNEL. K. R. Czarnecki and Jack E. 
Marte. May 1952. 24p. diagrs., photos. (NACA 
RM L52C24) 

INVESTIGATION OF THE VARIATION WITH 
REYNOLDS NUMBER OF THE BASE, WAVE, AND 
SKIN-FRICTION DRAG OF A PARABOLIC BODY OF 
REVOLUTION (NACA RM-10) AT MACH NUMBERS 
OF 1.62, 1.93, AND 2.41 IN THE LANGLEY 9-INCH 
SUPERSONIC TUNNEL. Eugene S. Love, Donald E. 
Coletti and August F. Bromm, Jr. October 1952. 
62p. diagrs., photos., (NACA RM L52H21) 

THE EFFECTS OF A SMALL JET OF AIR EX- 
HAUSTING FROM THE NOSE OF A BODY OF REV- 
OLUTION IN SUPERSONIC FLOW. Eugene S. Love. 
November 1952. 45p. diagrs., photos. (NACA 
RM L52I19a) 

THE ZERO-LIFT DRAG OF A SLENDER BODY OF 
REVOLUTION (NACA RM-10 RESEARCH MODEL) 
AS DETERMINED FROM TESTS IN SEVERAL WIND 
TUNNELS AND IN FLIGHT AT SUPERSONIC 
SPEEDS. Albert J. Evans. 1954. ii, 13p. 
diagrs., tab. (NACA Rept. 1160. Formerly 
TN 2944) 

ON THE THREE-DIMENSIONAL INSTABILITY OF 
LAMINAR BOUNDARY LAYERS ON CONCAVE 
WALLS, (ijber eine dreidimensionale Instabilitat 
laminarer Grenzschichten an konkaven Wanden). H. 
Gortler. June 1954. 32p. diagrs. (NACA TM 1375. 
Trans, from Gesellschaft der Wissenschaften zu 
Gottlngen, Nachrichten, Mathematik, v. 2, no. 1, 
1940) 

AN EXPLORATORY INVESTIGATION OF SKIN 
FRICTION AND TRANSITION ON THREE BODIES 
OF REVOLUTION AT A MACH NUMBER OF 1.61. 
John H. Hilton, Jr. and K. R. Czarnecki. June 
1954. 15p. diagrs. (NACA TN 3193) 

INVESTIGATION OF DISTRIBUTED SURFACE 
ROUGHNESS ON A BODY OF REVOLUTION AT A 
MACH NUMBER OF 1.61. K. R. Czarnecki, Ross 
B. Robinson and John H. Hilton, Jr. June 1954. 
35p. diagrs., photo., 2 tabs. (NACA TN 3230) 

HEAT, MASS, AND MOMENTUM TRANSFER FOR 
FLOW OVER A FLAT PLATE WITH BLOWING OR 
SUCTION. H. S. Mlckley, R. C. Ross, A. L. Squyers 
and W. E. Stewart, Massachusetts Institute of 
Technology. July 1954. ii, 149p. diagrs., photos., 
9 tabs. (NACA TN 3208) 

EXACT SOLUTIONS OF LAMINAR -BOUNDARY - 
LAYER EQUATIONS WITH CONSTANT PROPERTY 
VALUES FOR POROUS WALL WITH VARIABLE 
TEMPERATURE. Patrick L. Donoughe and John N. 
B. Livingood. September 1954. 42p. diagrs., 2 
tabs. (NACA TN 3151) 



AERODYNAMICS 
FUNDAMENTAL (1,1) 



Laminar Flow - Viscous (Cont. ) 



EXPERIMENTAL DETERMINATION OF BOUNDARY- 
LAYER TRANSITION ON A BODY OF REVOLUTION 
AT M = 3.5. James R. Jedllcka, Max E. Wilkins 
and Alvln Seiff. October 1954. 56p. diagrs., photos. 
(NACA TN 3342. Formerly RM A53L18) 



BOUNDARY-LAYER TRANSITION AT MACH 3.12 
WITH AND WITHOUT SINGLE ROUGHNESS 
ELEMENTS. Paul F. Brinich. December 1954. 
41 p. diagrs. (NACA TN 3267) 

THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF AERODYNAMIC -HEATING AND ISOTHER- 
MAL HEAT -TRANSFER PARAMETERS ON A 
HEMISPHERICAL NOSE WITH LAMINAR BOUNDARY 
LAYER AT SUPERSONIC MACH NUMBERS. 
Howard A. Stine and Kent Wanlass. December 1954. 
48p. diagrs., photo., tab. (NACA TN 3344) 



ANALYSIS OF LAMINAR FORCED-CONVECTION 
HEAT TRANSFER IN ENTRANCE REGION OF FLAT 
RECTANGULAR DUCTS. E. M. Sparrow. January 
1955. 42p. diagrs. (NACA TN 3331) 



SIMILAR SOLUTIONS FOR THE COMPRESSIBLE 
LAMINAR BOUNDARY LAYER WITH HEAT 
TRANSFER AND PRESSURE GRADIENT. Clarence 
B. Cohen and Eli Reshotko. February 1955. 67p. 
diagrs., 2 tabs. (NACA TN 3325) 



LAMINAR BOUNDARY LAYER BEHIND SHOCK 
ADVANCING INTO STATIONARY FLUID. Harold 
Mirels. March 1955. 25p. diagrs., 2 tabs. (NACA 
TN 3401) 

THE COMPRESSIBLE LAMINAR BOUNDARY LAYER 
WITH FLUID INJECTION. George M. Low. March 
1955. 29p. diagrs., 3 tabs. (NACA TN 3404) 

APPARATUS FOR MEASUREMENTS OF TIME AND 
SPACE CORRELATION. (Appareil de Mesures de la 
Correlation Dans le Temps et L'Espace). A. Favre, 
J. Gaviglio and R. Dumas. (Presented at eighth In- 
ternational Congress for Theoretical and Applied 
Mechanics, Istanbul, Aug., 1952) April 1955. 20p. 
diagrs., photos. (NACA TM 1371. Trans, from La 
Recherche Aeronautique, no. 31, Jan.-Feb., 1953, 
p. 37-44). 

THE COMPRESSIBLE LAMINAR BOUNDARY LA YER 
WITH HEAT TRANSFER AND ARBITRARY PRES- 
SURE GRADIENT. Clarence B. Cohen and Eli 
Reshotko. April 1955. 43p. diagrs., 2 tabs. (NACA 
TN 3326) 

A METHOD OF QUADRATURE FOR CALCULATION 
OF THE LAMINAR AND TURBULENT BOUNDARY 
LAYER IN CASE OF PLANE AND ROTATIONALLY 
SYMMETRICAL FLOW. (Ein Quadraturverlahren 
zur Berechnung der laminaren und turbulenten 
Relbungsschicht bei ebener und rotationssymmetri- 
scher Strdmung). E. Truckenbrodt. May 1955. 
40p. diagrs. (NACA TM 1379. Trans, from 
Ingenieur-Archiv, v. 20, no. 4, 1952, p. 16-228). 



SEPARATION, STABILITY, AND OTHER PROPER- 
TIES OF COMPRESSIBLE LAMINAR BOUNDARY 
LAYER WITH PRESSURE GRADIENT AND HEAT 
TRANSFER. Morris Morduchow and Richard G. 
Grape, Polytechnic Institute of Brooklyn. May 1955. 
45p. diagrs., 6 tabs. (NACA TN 3296) 



TURBULENT FLOW 
(1.1.3.2) 

AN 8-FOOT AXISYMMETRICAL FIXED NOZZLE 
FOR SUBSONIC MACH NUMBERS UP TO 0.99 AND 
FOR A SUPERSONIC MACH NUMBER OF 1.2. 
Virgil S. Ritchie, Ray H. Wright and Marshall P. . 
Tulin. February 23, 1950. 52p. diagrs., photos., 
2 tabs. (NACA RM L50A03a) 

INVESTIGATION OF A SIMPLE DEVICE FOR PRE- 
VENTING SEPARATION DUE TO SHOCK AND 
BOUNDARY-LAYER INTERACTION. Coleman duP. 
Donaldson. November 29, 1950. 34p. diagrs., 
photos. (NACA RM L50B02a) 

INVESTIGATION AT SUPERSONIC SPEEDS OF SOME 
OF THE FACTORS AFFECTING THE FLOW OVER A 
RECTANGULAR WING WITH SYMMETRICAL 
CIRCULAR-ARC SECTION AND 30-PERCENT- 
CHORD TRAILING-EDGE FLAP. K. R. Czarnecki 
and James N. Mueller. January 2, 1951. lllp. 
diagrs., photos. (NACA RM L50J18) 

EFFECTS OF SEVERAL ARRANGEMENTS OF REC- 
TANGULAR VORTEX GENERATORS ON THE 
STATIC -PRESSURE RISE THROUGH A SHORT 2:1 
DIFFUSER. E. Floyd Valentine and Raymond B. 
Carroll. February 20, 1951. 35p. diagrs., photos. 
(NACA RM L50L04) 

AVERAGE SKIN-FRICTION COEFFICIENTS FROM 
BOUNDARY-LAYER MEASUREMENTS IN FLIGHT 
ON A PARABOLIC BODY OF REVOLUTION (NACA 
RM-10) AT SUPERSONIC SPEEDS AND AT LARGE 
REYNOLDS NUMBERS. Charles B. Rumsey and J. 
Dan Loposer. March 7, 1951. 33p. diagrs., photo. 
(NACA RM L51B12) 

A PRELIMINARY INVESTIGATION OF COMBUSTION 
WITH ROTATING FLOW IN AN ANNULAR COM- 
BUSTION CHAMBER. Ira R. Schwartz. September 
1951. 18p. diagrs., photos. (NACA RM L51E25a) 

PRELIMINARY INVESTIGATION OF THE EFFECTS 
OF RECTANGULAR VORTEX GENERATORS ON 
THE PERFORMANCE OF A SHORT 1.9:1 
STRAIGHT -WALL ANNULAR DIFFUSER. Charles 
C. Wood. October 1951. 27p. diagrs., photo., tab. 
(NACA RM L51G09) 

PRELIMINARY INVESTIGATION OF THE DRAG 
CHARACTERISTICS OF THE NACA RM-10 MISSILE 
AT MACH NUMBERS OF 1.40 AND 1.59 IN THE 
LANGLEY 4- BY 4-FOOT SUPERSONIC TUNNEL. 
Lowell E. Hasel, Archibald R. Sinclair and Clyde V. 
Hamilton. April 1952. 49p. diagrs., photos, 3 tabs. 
(NACA RM L52A14) 

SKIN-FRICTION DRAG AND BOUNDARY- LAYER 
TRANSITION ON A PARABOLIC BODY OF REVO - 
LUTION (NACA RM-10) AT A MACH NUMBER OF 
1.6 IN THE LANGLEY 4- BY 4-FOOT SUPERSONIC 
PRESSURE TUNNEL. K. R. Czarnecki and Jack E. 
Marte. May 1952. 24p. diagrs., photos. (NACA 
RM L52C24) 

HEAT TRANSFER AND SKIN FRICTION FOR TUR- 
BULENT BOUNDARY LAYERS ON HEATED OR 
COOLED SURFACES AT HIGH SPEEDS. Coleman 
duP. Donaldson. October 1952. 20p. diagr., 
3 tabs. (NACA RM L52H04) 

INVESTIGATION OF THE VARIATION WITH 
REYNOLDS NUMBER OF THE BASE, WAVE, AND 
SKIN-FRICTION DRAG OF A PARABOLIC BODY OF 
REVOLUTION (NACA RM-10) AT MACH NUMBERS 
OF 1.62, 1.93, AND 2.41 IN THE LANGLEY 9-INCH 
SUPERSONIC TUNNEL. Eugene S. Love, Donald E. 
Coletti and August F. Bromm, Jr. October 1952. 
62p. diagrs., photos., (NACA RM L52H21) 



AERODYNAMICS 
10 FUNDAMENTAL (1. 1) 



Turbulent Flow - Viscous (Cont. ) 



THE EFFECTS OF A SMALL JET OF AIR EX- 
HAUSTING FROM THE NOSE OF A BODY OF REV- 
OLUTION IN SUPERSONIC FLOW. Eugene S. Love. 
November 1952. 45p. diagrs., photos. (NACA 
RM L52I19a) 

DIFFUSION OF HEAT FROM A LINE SOURCE IN 
ISOTROPIC TURBULENCE. Mahinder S. Uberoi 
and Stanley Corrsin, Johns Hopkins University. 
1953, 11, 29p. diagrs., photos., tab. (NACA 
Rept. 1142. Formerly TN 2710) 

AVERAGE SKIN-FRICTION COEFFICIENTS FROM 
BOUNDARY-LAYER MEASUREMENTS ON A OGIVE- 
CYLINDER BODY IN FLIGHT AT SUPERSONIC 
SPEEDS. J. Dan Loposer. January 1953. lip. 
diagrs., photo. (NACA RM L52K28a) 

THE ZERO-LIFT DRAG OF A SLENDER BODY OF 
REVOLUTION (NACA RM-10 RESEARCH MODEL) 
AS DETERMINED FROM TESTS IN SEVERAL WIND 
TUNNELS AND IN FLIGHT AT SUPERSONIC 
SPEEDS. Albert J. Evans. 1954. 11, 13p. 
diagrs., tab. (NACA Rept. 1160. Formerly 
TN 2944) 

AVERAGE SKIN-FRICTION DRAG COEFFICIENTS 
FROM TANK TESTS OF A PARABOLIC BODY OF 
REVOLUTION (NACA RM-10). Elmo J. Mottard and 
J. Dan Loposer. 1954. 11, 7p. diagrs., photos. 
(NACA Rept. 1161. Formerly TN 2854) 

CONVECTION OF A PATTERN OF VORTICITY 
THROUGH A SHOCK WAVE. H. S. Rlbner. 1954. 
11, 17p. diagrs. (NACA Rept. 1164. Formerly 
TN 2864) 

UNSTEADY OBLIQUE INTERACTION OF A SHOCK 
WAVE WITH A PLANE DISTURBANCE. Franklin K. 
Moore. 1954. 11, 21p. diagrs. (NACA Rept. 1165. 
Formerly TN 2879) 

SECONDARY FLOWS AND BOUNDARY-LAYER 
ACCUMULATIONS IN TURBINE NOZZLES. Harold 
E. Rohlik, Milton G. Kofskey, Hubert W. Allen and 
Howard Z. Herzig. 1954. 11, 32p. diagrs., photos., 
3 tabs. (NACA Rept. 1168. Formerly TN 2871; 
TN 2909; TN 2989) 

PRELIMINARY MEASUREMENTS OF TURBULENCE 
AND TEMPERATURE FLUCTUATIONS BEHIND A 
HEATED GRID. A. L. Klstler, V. O'Brien and S. 
Corrsin, Johns Hopkins University. June 1954. 
24p. diagrs., photo. (NACA RM 54D19) 

AN EXPLORATORY INVESTIGATION OF SKIN 
FRICTION AND TRANSITION ON THREE BODIES 
OF REVOLUTION AT A MACH NUMBER OF 1.61. 
John H. Hilton, Jr. and K. R. Czarnecki. June 
1954. 15p. diagrs. (NACA TN 3193) 

MEASUREMENT OF HEAT TRANSFER IN THE TUR- 
BULENT BOUNDARY LAYER ON A FLAT PLATE 
IN SUPERSONIC FLOW AND COMPARISON WITH 
SKIN-FRICTION RESULTS. C. C. Pappas. June 
1954. 32p. diagrs., tab. (NACA TN 3222) 

INVESTIGATION OF DISTRIBUTED SURFACE 
ROUGHNESS ON A BODY OF REVOLUTION AT A 
MACH NUMBER OF 1.61. K. R. Czarnecki, Ross 
B. Robinson and John H. Hilton, Jr. June 1954. 
35p. diagrs., photo., 2 tabs. (NACA TN 3230) 

A NEW HODOGRAPH FOR FREE-STREAMLINE 
THEORY. Anatol Roshko, California Institute of 
Technology. July 1954. 39p. diagrs., 3 tabs. 
(NACA TN 3168) 



ON THE DRAG AND SHEDDING FREQUENCY OF 
TWO-DIMENSIONAL BLUFF BODIES. Anatol 
Roshko, California Institute of Technology. 
July 1954. 29p. diagrs., tab. (NACA TN 3169) 

CHARACTERISTICS OF TURBULENCE IN A BOUND- 
ARY LAYER WITH ZERO PRESSURE GRADIENT. 
P. S. Klebanoff, National Bureau of Standards. July 
1954. 56p. diagrs. (NACA TN 3178) 

HEAT, MASS, AND MOMENTUM TRANSFER FOR 
FLOW OVER A FLAT PLATE WITH BLOWING OR 
SUCTION. H. S. Mickley, R. C. Ross, A. L. Squyers 
and W. E. Stewart, Massachusetts Institute of 
Technology. July 1954. ii, 149p. diagrs., photos., 
9 tabs. (NACA TN 3208) 

SHOCK-TURBULENCE INTERACTION AND THE 
GENERATION OF NOISE. H. S. Rlbner. July 1954. 
60p. diagrs., tab. (NACA TN 3255) 

EXAMINATION OF THE EXISTING DATA ON THE 
HEAT TRANSFER OF TURBULENT BOUNDARY 
LAYERS AT SUPERSONIC SPEEDS FROM THE 
POINT OF VIEW OF REYNOLDS ANALOGY. Alvin 
Seiff. August 1954. 38p. diagrs., tab. (NACA 
TN 3284) 



HEAT TRANSFER FROM A HEMISPHERE - 
CYLINDER EQUIPPED WITH FLOW -SEPARATION 
SPIKES. Jackson R. Stalder and Helmer V. Nielsen. 
September 1954. 29p. diagrs., photos. (NACA 
TN 3287) 

TURBULENT-HEAT -TRANSFER MEASUREMENTS 
AT A MACH NUMBER OF 3.03. Maurice J. 
Brevoort and Bernard Rashis. September 1954. 
21p. diagrs., tab. (NACA TN 3303) 

•EXPERIMENTAL DETERMINATION OF BOUNDARY- 
LAYER TRANSITION ON A. BODY OF REVOLUTION 
AT M = 3.5. James R. Jedlicka, Max E. Wilkins 
and Alvin Seiff. October 1954. 5?p. diagrs., photos. 
(NACA TN 3342. Formerly RM A53L18) 

BOUNDARY-LAYER TRANSITION AT MACH 3.12 
WITH AND WITHOUT SINGLE ROUGHNESS 
ELEMENTS. Paul F. Brinich. December 1954. 
41 p. diagrs. (NACA TN 3267) 

AN ANALYTICAL ESTIMATION OF THE EFFECT 
OF TRANSPIRATION COOLING ON THE HEAT- 
TRANSFER AND SKIN-FRICTION CHARACTER- 
ISTICS OF A COMPRESSIBLE TURBULENT 
BOUNDARY LAYER. Morris W. Rubesln. 
December 1954. 56p. diagrs. (NACA TN 3341) 

STUDY OF THE MOMENTUM DISTRIBUTION OF 
TURBULENT BOUNDARY LAYERS IN ADVERSE 
PRESSURE GRADIENTS. Virgil A. Sandborn and 
Raymond J. Slogar. January 1955. 79p. diagrs., 
photos. (NACA TN 3264) 

EXPERIMENTAL EVALUATION OF MOMENTUM 
TERMS IN TURBULENT PIPE FLOW. Virgil A. 
Sandborn. January 1955. 40p. diagrs. (NACA 
TN 3266) 

SOME MEASUREMENTS OF TIME AND SPACE 
CORRELATION IN WIND TUNNEL. (Quelques 
Mesures de Correlation Dans le Temps et L'Espace 
en Soufflerie). A. Favre, J. GavigUo and R. Dumas. 
February 1955. 21p. diagrs. (NACA TM 1370. 
Trans, from La Recherche Aeronautique, no. 32, 
Mar. -Apr., 1953, p. 21-28). 



AERODYNAMICS 
FUNDAMENTAL (1,1) 



11 



Turbulent Flow - Viscous (Cont. ) 

EXPERIMENTS ON TURBULENT FLOW THROUGH 
CHANNELS HAVING POROUS ROUGH SURFACES 
WITH OR WITHOUT AIR INJECTION. E. R. G. 
Eckert, Anthony J. Diaguila and Patrick L. 
Donoughe. February 1955. 45p. diagrs., photos., 
tab. (NACA TN 3339) 

TURBULENT-HEAT-TRANSFER MEASUREMENTS 
AT A MACH NUMBER OF 2.06. Maurice J. 
Brevoort and Bernard Rashis. March 1955. 20p. 
diagrs., tab. (NACA TN 3374) 

FREE -FLIGHT MEASUREMENTS OF TURBULENT- 
BOUNDARY- LAYER SKIN FRICTION IN THE PRE- 
SENCE OF SEVERE AERODYNAMIC HEATING AT 
MACH NUMBERS FROM 2.8 TO 7.0. Simon C. 
Sommer and Barbara J. Short. March 1955. 47p. 
diagrs., photos., 2 tabs. (NACA TN 3391) 

INVESTIGATION OF THE TURBULENT BOUNDARY 
LAYER ON A YAWED FLAT PLATE. Harry 
Ashkenas and Frederick R. Riddell, Cornell 
University. April 1955. 57p. diagrs., photos. 
(NACA TN 3383) 

A SELF-EXCITED, ALTERNATING-CURRENT, 
CONSTANT -TEMPERATURE HOT-WIRE ANEMOM- 
ETER. Charles E. Shepard. April 1955. 29p. 
diagrs., photos. (NACA TN 3406) 

A METHOD OF QUADRATURE FOR CALCULATION 
OF THE LAMINAR AND TURBULENT BOUNDARY 
LAYER IN CASE OF PLANE AND ROTATIONALLY 
SYMMETRICAL FLOW. (Ein Quadraturverfahren 
zur Berechnung der laminaren und turbulenten 
Reibungsschicht bei ebener und rotationssymmetri- 
scher Strdmung). E. Truckenbrodt. May 1955. 
40p. diagrs. (NACA TM 1379. Trans, from 
Ingenieur-Archiv, v. 20, no. 4, 1952., p. 16-228). 

ANALYSIS OF FULLY DEVELOPED TURBULENT 
HEAT TRANSFER AND FLOW IN AN ANNULUS 
WITH VARIOUS ECCENTRICITIES. Robert G. 
Deissler and Maynard F. Taylor. May 1955. 42p. 
diagrs. (NACA TN 3451) 

LONGITUDINAL TURBULENT SPECTRUM SURVEY 
OF BOUNDARY LAYERS IN ADVERSE PRESSURE 
GRADIENTS. Virgil A. Sandborn and Raymond J. 
Slogar. May 1955. 40p. diagrs., tab. (NACA 
TN 3453) 

EFFECT OF A DISCONTINUITY ON TURBULENT 
BOUNDARY-LAYER-THICKNESS PARAMETERS 
WITH APPLICATION TO SHOCK-INDUCED SEPARA- 
TION. Eli Reshotko and Maurice Tucker. May 1955. 
21p. diagrs. (NACA TN 3454) 

JET MIXING 
(1. 1.3.3) 

VELOCITY AND TEMPERATURE FIELDS IN CIR- 
CULAR JET EXPANDING FROM CHOKED NOZZLE 
INTO QUIESCENT AIR. Morris D. Rousso and 
Fred D. Kochendorfer. July 1951. 34p. diagrs., 
photos. (NACA RM E51F18. Formerly 
RM E50E03a) 

THE EFFECTS OF A SMALL JET OF AIR EX- 
HAUSTING FROM THE NOSE OF A BODY OF REV- 
OLUTION IN SUPERSONIC FLOW. Eugene S. Love. 
November 1952. 45p. diagrs., photos. (NACA 
RM L52I19a) 

THE NEAR NOISE FIELD OF STATIC JETS AND 
SOME MODEL STUDIES OF DEVICES FOR NOISE 
REDUCTION. Leslie W. Lassiter and Harvey H. 
Hubbard. July 1954. 38p. diagrs., photos. (NACA 
TN3187) 



STARTING AND OPERATING LIMITS OF TWO 
SUPERSONIC WIND TUNNELS UTILIZING AUXIL- 
IARY AIR INJECTION DOWNSTREAM OF THE 
TEST SECTION. Henry R. Hunczak and Morris D. 
Rousso. September 1954. 28p. diagrs., photo. 
(NACA TN 3262) 

APPROXIMATE EFFECT OF LEADING-EDGE 
THICKNESS, INCIDENCE ANGLE, AND INLET 
MACH NUMBER ON INLET LOSSES FOR HIGH- 
SOLIDITY CASCADES OF LOW CAMBERED 
BLADES. Linwood C. Wright. December 1954. 
38p. diagrs. (NACA TN 3327) 

THEORY OF THE JET SYPHON. B. Szczenlowski, 
University of Montreal. May 1955. 49p. diagrs., 
3 tabs. (NACA TN 3385) 



AERODYNAMICS WITH HEAT 
(1.1.4) 

METHOD FOR RAPID DETERMINATION OF PRES- 
SURE CHANGE FOR ONE-DIMENSIONAL FLOW 
WITH HEAT TRANSFER, FRICTION, ROTATION, 
AND AREA CHANGE. James E. Hubbartt, Henry O. 
Slone and Vernon L. Arne. June 1954. 22p. diagrs., 
2 tabs. (NACA TN 3150) 

EXPERIMENTAL INVESTIGATION OF TEMPERA- 
TURE RECOVERY FACtORS ON A 10° CONE AT 
ANGLE OF ATTACK AT A MACH NUMBER OF 3. 12. 
John R. Jack and Barry Moskowitz. July 1954. 15p. 
diagrs. (NACA TN 3256) 

TRANSVERSE OSCILLATIONS IN A CYLINDRICAL 
COMBUSTION CHAMBER. Franklin K. Moore and 
Stephen H. Maslen. October 1954. 25p. diagrs. 
(NACA TN 3152) 

THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF AERODYNAMIC -HEATING AND ISOTHER- 
MAL HEAT -TRANSFER PARAMETERS'ON A 
HEMISPHERICAL NOSE WITH LAMINAR BOUNDARY 
LAYER AT SUPERSONIC MACH NUMBERS. 
Howard A. Stine and Kent Wanlass. December 1954. 
48p. diagrs., photo., tab. (NACA TN 3344) 

ONE-DIMENSIONAL CALCULATION OF FLOW IN A 
ROTATING PASSAGE WITH EJECTION THROUGH A 
POROUS WALL. E. R. G. Eckert, John N. B. 
Livingood and Ernst I. Prasse. March 1955. 29p. 
diagrs., photo. (NACA TN 3408) 

EFFECT OF DISSOCIATION ON THERMODYNAMIC 
PROPERTIES OF PURE DIATOMIC GASES. Harold 
W. WooUey, National Bureau of Standards. April 
1955. 19p. diagrs., tab. (NACA TN 3270) 

HEATING 

(1.1.4.1) ^ 

AN EXPLORATORY INVESTIGATION OF SKIN 
FRICTION AND TRANSITION ON THREE BODIES 
OF REVOLUTION AT A MACH NUMBER OF 1.61. 
John H. Hilton, Jr. and K. R. Czarnecki. June 
1954. 15p. diagrs. (NACA TN 3193) 

MEASUREMENT OF HEAT TRANSFER IN THE TUR- 
BULENT BOUNDARY LAYER ON A FLAT PLATE 
IN SUPERSONIC FLOW AND COMPARISON WITH 
SKIN-FRICTION RESULTS. C. C. Pappas. June 
1954. 32p. diagrs., tab. (NACA TN 3222) 



AERODYNAMICS 
12 FUNDAMENTAL, (1. 



1) 



Heating - Aerodynamic (Cont. ) 

INVESTIGATION OF DISTRIBUTED SURFACE 
ROUGHNESS ON A BODY OF REVOLUTION AT A 
MACH NUMBER OF 1.61. K. R. Czarnecki, Ross 
B. Robinson and John H. Hilton, Jr. June 1954. 
35p. dlagrs., photo., 2 tabs. (NACA TN 3230) 

HEAT TRANSFER FROM A HEMISPHERE - 
CYUNDER EQUIPPED WITH FLOW -SEPARATION 
SPIKES. Jackson R. Stalder and Helmer V. Nielsen. 
September 1954. 29p. diagrs., photos. (NACA 
TN 3287) 

THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF AERODYNAMIC -HEATING AND ISOTHER- 
MAL HEAT -TRANSFER PARAMETERS ON A 
HEMISPHERICAL NOSE WITH LAMINAR BOUNDARY 
LAYER AT SUPERSONIC MACH NUMBERS. 
Howard A. Stine and Kent Wanlass. December 1954. 
48p. diagrs., photo., tab. (NACA TN 3344) 

ICING LIMIT AND WET -SURFACE TEMPERATURE 
VARIATION FOR TWO AIRFOIL SHAPES UNDER 
SIMULATED HIGH-SPEED FLIGHT CONDITIONS. 
Willard D. Coles. February 1955. 33p. diagrs., 
photos. (NACA TN 3396) 

HEAT TRANSFER 
(1, 1.4.2) 

INVESTIGATION OF POWER REQUIREMENTS FOR 
ICE PREVENTION AND CYCLICAL DE-ICING OF 
INLET GUIDE VANES WITH INTERNAL ELECTRIC 
HEATERS. Uwe von Glahn and Robert E. Blatz. 
December 1, 1950. 49p. diagrs., photos. (NACA 
RM E50H29) 

ICING CHARACTERISTICS AND ANTI-ICING HEAT 
REQUIREMENTS FOR HOLLOW AND INTERNALLY 
MODIFIED GAS-HEATED INLET GUIDE VANES. 
Vernon H. Gray and Dean T. Bowden. December 5, 

1950. 49p. diagrs., photos. (NACA RM E50I08) 

CORRELATION OF SUPERSONIC CONVECTIVE 
HEAT -TRANSFER COEFFICIENTS FROM MEAS- 
UREMENTS OF THE SKIN TEMPERATURE OF A 
PARABOLIC BODY OF REVOLUTION (NACA RM-10). 
Leo T. Chauvin and Carlos A. deMoraes. March 7, 

1951. 39p. diagrs., photo. 2 tabs. (NACA 
RM L51A18) 

SKIN-TEMPERATURE TELEMETER FOR 
DETERMINING BOUNDARY-LAYER HEAT- 
TRANSFER COEFFICIENTS. Clifford L. Fricke 
and Francis B. Smith. March 15, 1951. 22p. 
diagrs. (NACA RM L50J17) 

A SUMMARY OF AVAILABLE KNOWLEDGE CON- 
CERNING SKIN FRICTION AND HEAT TRANSFER 
AND ITS APPLICATION TO THE DESIGN OF HIGH- 
SPEED MISSILES. Morris W. Rubesln, Charles B. 
Rumsey and Steven A. Varga. November 1951. 17p. 
diagrs. (NACA RM A51J25a) 

EXPERIMENTAL INVESTIGATION OF AIR-FLOW 
UNIFORMITY AND PRESSURE LEVEL ON WIRE 
CLOTH FOR TRANSPIRATION-COOLING APPLICA- 
TKJNS. Patrick L. Donoughe and Roy A. McKlnnon. 
July 1952. 28p. diagrs., photos., tab. (NACA 
RM E52E16) 

HEAT TRANSFER AND SKIN FRICTION FOR TUR- 
BULENT BOUNDARY LAYERS ON HEATED OR 
COOLED SURFACES AT HIGH SPEEDS. Coleman 
duP. Donaldson. October 1952. 20p. diagr., 
3 tabs. (NACA RM L52H04) 

COMPARISON OF EFFECTIVENESS OF 
CONVECTION-, TRANSPIRATION-, AND FILM- 
COOLING METHODS WITH AIR AS COOLANT. 
E. R. G. Eckert and John N. B. Livingood. 1954. 
ii, 17p. diagrs. (NACA Rept. 1182. Formerly 
TN 3010) 



MEASUREMENT OF HEAT TRANSFER IN THE TUR- 
BULENT BOUNDARY LAYER ON A FLAT PLATE 
IN SUPERSONIC FLOW AND COMPARISON WITH 
SKIN-FRICTION RESULTS. C. C. Pappas. June 
1954. 32p. diagrs., tab. (NACA TN 3222) 

HEAT, MASS, AND MOMENTUM TRANSFER FOR 
FLOW OVER A FLAT PLATE WITH BLOWING OR 
SUCTION. H. S. Mickley, R. C. Ross, A. L. Squyers 
and W. E. Stewart, Massachusetts Institute of 
Technology. July 1954. ii, 149p. diagrs., photos., 
9 tabs. (NACA TN 3208) 

EXPERIMENTAL INVESTIGATION OF TEMPERA- 
TURE RECOVERY FACTORS ON A 10° CONE AT 
ANGLE OF ATTACK AT A MACH NUMBER OF 3.12. 
John R. Jack and Barry Moskowitz. July 1954. 15p. 
diagrs. (NACA TN 3256) 

EXAMINATION OF THE EXISTING DATA ON THE 
HEAT TRANSFER OF TURBULENT BOUNDARY 
LAYERS AT SUPERSONIC SPEEDS FROM THE 
POINT OF VIEW OF REYNOLDS ANALOGY. Alvln 
Seiff. August 1954. 38p. diagrs., tab. (NACA 
TN 3284) 

RECOVERY CORRECTIONS FOR BUTT -WELDED, 
STRAIGHT-WIRE THERMOCOUPLES IN HIGH- 
VELOCITY, HIGH-TEMPERATURE GAS STREAMS. 
Frederick S. Simmons. September 1954. 19p. 
diagrs. (NACA RM E54G22a) 

EXACT SOLUTIONS OF LAMINAR-BOUNDARY- 
LAYER EQUATIONS WITH CONSTANT PROPERTY 
VALUES FOR POROUS WALL WITH VARIABLE 
TEMPERATURE. Patrick L. Donoughe and John N. 
B. Livingood. September 1954. 42p. diagrs., 2 
tabs. (NACA TN 3151) 

HEAT TRANSFER FROM A HEMISPHERE- 
CYLINDER EQUIPPED WITH FLOW -SEPARATION 
SPIKES. Jackson R. Stalder and Helmer V. Nielsen. 
September 1954. 29p. diagrs., photos. (NACA 
TN 3287) I 

TURBULENT-HEAT -TRANSFER MEASUREMENTS 
AT A MACH NUMBER OF 3.03. Maurice J. 
Brevoort and Bernard Rashis. September 1954. 
21p. diagrs., tab. (NACA TN 3303) 

SHEARING-STRESS MEASUREMENTS BY USE OF A 
HEATED ELEMENT. H. W. Liepmann and G. T. 
Skinner, California Institute of Technology. 
November 1954. 27p. diagrs. (NACA TN 3268) 



AN ANALYTICAL ESTIMATION OF THE EFFECT 
OF TRANSPIRATION COOLING ON THE HEAT- 
TRANSFER AND SKIN-FRICTION CHARACTER- 
ISTICS OF A COMPRESSIBLE TURBULENT 
BOUNDARY LAYER. Morris W. Rubesln. 
December 1954. 56p. diagrs. (NACA TN 3341) 

THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF AERODYNAMIC -HEATING AND ISOTHER- 
MAL HEAT -TRANSFER PARAMETERS ON A 
HEMISPHERICAL NOSE WITH LAMINAR BOUNDARY 
LAYER AT SUPERSONIC MACH NUMBERS. 
Howard A. Stine and Kent Wanlass. December 1954. 
48p. diagrs., photo., tab. (NACA TN 3344) 

SIMILAR SOLUTIONS FOR THE COMPRESSIBLE 
LAMINAR BOUNDARY LAYER WITH HEAT 
TRANSFER AND PRESSURE GRADIENT. Clarence 
B. Cohen and Ell Reshotko. February 1955. 67p. 
diagrs., 2 tabs. (NACA TN 3325) 



AERODYNAMICS 
FUNDAMENTAL (1.1) 



13 



Heat Transfer - Aerodynamic (Cont. ) 

ICING LIMIT AND WET-SURFACE TEMPERATURE 
VARIATION FOR TWO AIRFOIL SHAPES UNDER 
SIMULATED HIGH-SPEED FLIGHT CONDITIONS. 
Willard D. Coles. February 1955. 33p. diagrs., 
photos. (NACA TN 3396) 

TURBULENT -HEAT -TRA NSFER MEASUREMENTS 
AT A MACH NUMBER OF 2.06. Maurice J. 
Brevoort and Bernard Rashis. March 1955. 20p. 
diagrs., tab. (NACA TN 3374) 



A THEORY FOR PREDICTING THE FLOW OF REAL 
GASES IN SHOCK TUBES WITH EXPERIMENTAL 
VERIFICATION. Robert L. Trimpi and Nathaniel B. 
Cohen. March 1955. 69p. diagrs., photo. 
(NACA TN 3375) 

FREE -FLIGHT MEASUREMENTS OF TURBULENT- 
BOUNDARY- LAYER SKIN FRICTION IN THE PRE- 
SENCE OF SEVERE AERODYNAMIC HEATING AT 
MACH NUMBERS FROM 2.8 TO 7.0. Simon C. 
Sommer and Barbara J. Short. March 1955. 47p. 
diagrs., photos., 2 tabs. (NACA TN 3391) 

THE COMPRESSIBLE LAMINAR BOUNDARY LAYER 
WITH FLUID INJECTION. George M. Low. March 
1955. 29p. diagrs., 3 tabs. (NACA TN 3404) 

THE COMPRESSIBLE LAMINAR BOUNDARY LAYER 
WJTH HEAT TRANSFER AND ARBITRARY PRES- 
SURE GRADIENT. Clarence B. Cohen and Eli 
Reshotko. April 1955. 43p. diagrs., 2 tabs. (NACA 
TN 3326) 

ANALYTIC DETERMINATION OF THE DISCHARGE 
COEFFICIENTS OF FLOW NOZZLES. Frederick S. 
Simmons. April 1955. 15p. diagrs. (NACA 
TN 3447) 

SEPARATION, STABILITY, AND OTHER PROPER- 
TIES OF COMPRESSIBLE LAMINAR BOUNDARY 
LAYER WITH PRESSURE GRADIENT AND HEAT 
TRANSFER. Morris Morduchow and Richard G. 
Grape, Polytechnic Institute of Brooklyn. May 1955. 
45p. diagrs., 6 tabs. (NACA TN 3296) 



ADDITIONS OF HEAT 
(1. 1.4. 3) 



A PRELIMINARY INVESTIGATION OF COMBUSTION 
WITH ROTATING FLOW IN AN ANNULAR COM- 
BUSTION CHAMBER. Ira R. Schwartz. September 
1951. 18p. diagrs., photos. (NACA RM L51E25a) 



PRESSURE DISTRIBUTION AND AERODYNAMIC 
COEFFICIENTS ASSOCIATED WITH HEAT ADDI- 
TION TO SUPERSONIC AIR STREAM ADJACENT TO 
TWO-DIMENSIONAL SUPERSONIC WING. I. Irving 
Pinkel, John S. Seratini and John L. Gregg. February 
1952. 33p. diagrs., tab. (NACA RM E51K26) 



AN ANALYSIS OF BUZZING IN SUPERSONIC RAM 
JETS BY A MODIFIED ONE -DIMENSIONAL NON- 
STATIONARY WAVE THEORY. Robert L. Trimpi. 
March 1952. ?2p. diagrs., photos. (NACA 
RM LS2A18) 

DIFFUSION OF HEAT FROM A LINE SOURCE IN 
ISOTROPIC TURBULENCE. Mahinder S. Uberoi 
and Stanley Corrsin, Johns Hopkins University. 
1953, ii, 29p. diagrs., photos., tab. (NACA 
Rept. 1142. Formerly TN 2710) 



PRELIMINARY MEASUREMENTS OF TURBULENCE 
AND TEMPERATURE FLUCTUATIONS BEHIND A 
HEATED GRID. A. L. Kistler, V. O'Brien and S. 
Corrsin, Johns Hopkins University. June 1954. 
24p. diagrs., photo. (NACA RM 54D19) 

HEAT, MASS, AND MOMENTUM TRANSFER FOR 
FLOW OVER A FLAT PLATE WITH BLOWING OR 
SUCTION. H. S. Mickley, R. C. Ross, A. L. Squyers 
and W. E. Stewart, Massachusetts Institute of 
Technology. July 1954. ii, 149p. diagrs., photos., 
9 tabs. (NACA TN 3208) 



EXPERIMENTAL HEAT -TRANSFER AND FRICTION 
COEFFICIENTS FOR AIR FLOWING THROUGH 
STACKS OF PARALLEL FLAT PLATES. Eldon W. 
Sams and Walter F. Weiland, Jr. August 1954. 33p. 
diagrs., photo., tab. (NACA RM E54F11) 



KINETIC TREATMENT OF THE NUCLEATION IN 
SUPERSATURATED VAPORS. (Kinetische 
Behandlung der Keimbildung in ubersattigten 
Dampfen). R. Becker and W. Doring. September 
1954. 43p. diagrs. (NACA TM 1374. Trans, from 
Annalen der Physik, Ser.5, v. 24, 1935, p. 719-752). 

THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF .AERODYNAMIC -HEATING AND ISOTHER- 
MAL HEAT -TRANSFER PARAMETERS ON A 
HEMISPHERICAL NOSE WITH LAMINAR BOUNDARY 
LAYER AT SUPERSONIC MACH NUMBERS. 
Howard A. Stine and Kent Wanlass. December 1954. 
48p. diagrs., photo., tab. (NACA TN 33,44) 

A THEORY FOR PREDICTING THE FLOW OF REAL 
GASES IN SHOCK TUBES WITH EXPERIMENTAL 
VERIFICATION. Robert L. Trimpi and Nathaniel B. 
Cohen. March 1955. 69p. diagrs., photo. 
(NACA TN 3375) 

INTERACTION OF A FREE FLAME FRONT WITH A 
TURBULENCE FIELD. Maurice Tucker. March 1955. 
55p. diagrs., 2 tabs. (NACA TN 3407) 



FLOW OF RAREFIED GASES 
(l.l.S) 

VISCOSITY CORRECTIONS TO CONE PROBES IN 
RAREFIED SUPERSONIC FLOW AT A NOMINAL 
MACH NUMBER OF 4. L. Talbot, University of 
California. November 1954. 39p. diagrs., photo., 
4 tabs. (NACA TN 3219) 



14 AERODYNAMICS 



Wings 
(1.2) 



WING SECTIONS 
(1.2.1) 



WING-FLOW INVESTIGATION OF THE CHARAC- 
TERISTICS OF SEVEN UNSWEPT, UNTAPERED 
AIRFOILS OF ASPECT RATIO 8.0. Harold L. Crane 
and James J. Adams. June 13, 1951. 54p. diagrs., 
photo. (NACARM L51D24a) 



EXPERIMENTAL INVESTIGATION OF THE EF- 
FECTS OF VORTEX GENERATORS ON THE MAXI- 
MUM LIFT OF A 6-PERCENT -THICK SYMMETRI- 
CAL CIRCULAR-ARC AIRFOIL SECTION. WiUiam 
J. Bursnall. October 1952. 16p. diagrs., 2 tabs. 
(NACA RM L52G24) 



SECTION THEORY 
(1.2.1. 1) 



THE SUBSONIC AERODYNAMIC CHARACTERISTICS 
OF TWO DOUBLE -WEDGE AIRFOIL SECTIONS 
SUITABLE FOR SUPERSONIC FUGHT. Joseph 
Solomon and Floyd W. Henney. May 12, 1947. 33p. 
diagrs., pliotos. (NACA RM A6G24) 

APPLICATION OF ONE PART OF VON KARMAN'S 
TWO-DIMENSIONAL TRANSONIC SIMILARITY LAW 
TO DRAG DATA OF NACA 65 -SERIES WINGS. 
Kenneth B. Amer. August 24, 1948. 9p. diagrs. 
(NACA RM L8F24) 



INVESTIGATION AT MACH NUMBER 1.62 OF THE 
PRESSURE DISTRIBUTION OVER A RECTANGULAR 
WING WITH SYMMETRICAL CIRCULAR-ARC SEC- 
TION AND 30-PERCENT -CHORD TRAILING-EDGE 
FLAP. K. R. Czarnecki and James N. Mueller. 
January 25, 1950. Sip. diagrs., photos. (NACA 
RM L9J05) 

INVESTIGATION AT SUPERSONIC SPEEDS OF SOME 
OF THE FACTORS AFFECTING THE FLOW OVER A 
RECTANGULAR WING WITH SYMMETRICAL 
CIRCULAR-ARC SECTION AND 30-PERCENT- 
CHORD TRAILING-EDGE FLAP. K. R. Czarnecki 
and James N. Mueller. January 2, 1951. lllp. 
diagrs., photos. (NACA RM L50J18) 



ON THE APPLICATION OF TRANSONIC SIMILARITY 
RULES TO WINGS OF FINITE SPAN. John R. 
Spreiter. 1953. ii, 21p. diagrs. (NACA Rept. 1153. 
Formerly TN 2726) 

THEORETICAL STUDY OF THE TRANSONIC LIFT 
OF A DOUBLE -WEDGE PROFILE WITH DETACHED 
BOW WAVE. Walter G. Vincenti and Cleo B. 
Wagoner. (Portions of this work were reported at 
the eighth International Congress on Theoretical and 
Applied Mechanics, Istanbul, Turkey, August 20-28, 
1952). 1954. ii, 24p. diagrs., 2 tabs. (NACA 
Rept. 1180. Formerly TN 2832) 



TABLES FOR THE COMPUTATION OF WAVE DRAG 
OF ARROW WINGS OF ARBITRARY AIRFOIL SEC- 
TION. Frederick C. Grant and Morton Cooper. 
June 1954. 9p. diagr., 28p. tabs, (in pocket) (NACA 
TN 3185) 



STUDY OF THE SUBSONIC FORCES AND MOMENTS 
ON AN INCLINED PLATE OF INFINITE SPAN. 
Bradford H. Wick. June 1954. 25p. diagrs. (NACA 
TN 3221) 

AN EXPERIMENTAL STUDY OF THE LIFT AND 
PRESSURE DISTRIBUTION ON A DOUBLE -WEDGE 
PROFILE AT MACH NUMBERS NEAR SHOCK 
ATTACHMENT. Walter G. Vincenti, Duane W. Dugan 
and E. Ray Phelps. July 1954. 43p. diagrs. 
(NACA TN 3225) 

AN INVESTIGATION OF A LIFTING 10-PERCENT- 
THICK SYMMETRICAL DOUBLE-WEDGE AJRFOIL 
AT MACH NUMBERS UP TO 1. Milton D. 
Humphreys. November 1954. 35p. diagrs., photos., 
tab. (NACA TN 3306) 

SUBSONIC EDGES IN THIN-WING AND SLENDER- 
BODY THEORY. Milton D. Van Dyke. November 

1954. 26p. diagrs. (NACA TN 3343) 

DESCRIPTION AND ANALYSIS OF A ROCKET - 
VEHICLE EXPERIMENT ON FLUTTER INVOLVING 
WING DEFORMATION AND BODY MOTIONS. H. J. 
Cunningham and R. R. Lundstrom. January 1955. 
26p. diagrs., photos., 2 tabs. (NACA TN 3311. 
Formerly RM L50I29) 

SOME CONSIDERATIONS ON TWO-DIMENSIONAL 
THIN AIRFOILS DEFORMING IN SUPERSONIC 
FLOW. Eugene Migotsky. January 1955. 36p. 
diagrs. (NACA TN 3386) 

LIFT ON A BENT, FLAT PLATE. (Auftrieb einer 
geknickten ebenen Platte). F. Keune. February 

1955. 15p. diagrs. (NACA TM 1340. Trans, from 
Bericht der Aerodynamischer Versuchsanstalt 
Gbttingen. Luttfahrtforschung, Mar. 20, 1936, 
Annual Volume, p. 85-87) 

SECOND-ORDER SUBSONIC AIRFOIL -SECTION 
THEORY AND ITS PRACTICAL APPLICATION. 
Milton D. Van Dyke. March 1955. 50p. diagrs., 
5 tabs. (NACA TN 3390) 



SECTION VARIABLES 
(1.2.1.2) 



PRESSURE-DISTRIBUTION DATA FOR THE NACA 
64i-012AND64lA012 AIRFOILS AT HIGH SUBSONIC 
MACH NUMBERS. Milton D. Humphreys. May 6, 
1949. 37p. photos. , diagrs. , 8 tabs. (NACA 
RM L9C18) 

EXPLORATORY INVESTIGATION AT HIGH AND 
LOW SUBSONIC MACH NUMBERS OF TWO EXPERI- 
MENTAL 6-PERCENT-THICK AIRFOIL SECTIONS 
DESIGNED TO HAVE HIGH MAXIMUM LIFT COEF- 
FICIENTS. Laurence K. Loftin, Jr. and Albert E. 
von Doenhoff. December 1951. 48p. diagrs., photo., 
2 tabs. (NACA RM L51F06) 



AERODYNAMICS 
WINGS (1.2) 



15 



Section Variables - Wing Sections 
(Cont. ) 

AERODYNAMIC CHARACTERISTICS OF THE NACA 
64-010 AND 0010-1.10 40/1.051 AIRFOIL SECTIONS 
AT MACH NUMBERS FROM 0.30 TO 0.85 AND 
REYNOLDS NUMBERS FROM 4.0 x 10° TO 8.0 X 10°. 
Laurence K. Loftin, Jr. August 1954. 17p. diagrs., 
tab. (NACA TN 3244) 

AN INVESTIGATION OF A LIFTING 10-PERCENT- 
THICK SYMMETRICAL DOUBLE-WEDGE AIRFOIL 
AT MACH NUMBERS UP TO 1. Milton D. 
Humphreys. November 1954. 35p. diagrs., photos., 
tab. (NACA TN 3306) 

Camber 
(1.2. 1.2.1) 

WING-FLOW INVESTIGATION OF THE CHARAC- 
TERISTICS OF SEVEN UNSWEPT, UNTAPERED 
AIRFOILS OF ASPECT RATIO 8.0. Harold L. Crane 
and James J. Adams. June 13, 1951. S4p. diagrs., 
photo. (NACA RM L51D24a) 

SMALL-SCALE TRANSONIC INVESTIGATION OF 
THE EFFECTS OF PARTIAL-SPAN LEADING-EDGE 
CAMBER ON THE AERODYNAMIC CHARACTERIS- 
TICS OF A 50° 38' SWEPTBACK WING OF ASPECT 
RATIO 2.98. William J. AUord, Jr. and Andrew L. 
Byrnes, Jr. June 1952. 28p. diagrs., photo., tab. 
(NACA RM L52D08a) 

THE EFFECTS OF CAMBER AND LEADING-EDGE- 
FLAP DEFLECTION ON THE PRESSURE PULSA- 
TIONS ON THIN RIGID AIRFOILS AT TRANSONIC 
SPEEDS. Milton D. Humphreys and John D. Kent. 
October 1952. 26p. diagrs., photos., tab. (NACA 
RM L52G22) 

EFFECT OF THICKNEffi, CAMBER, AND THICK- 
NESS DISTRIBUTION ON AIRFOIL CHARACTERIS- 
TICS AT MACH NUMBERS UP TO 1.0. Bernard N. 
Daley and Richard S. Dick. October 1952. 76p. 
photos., diagrs., tab. (NACA RM L52G31a) 



DESIGN CONSIDERATIONS FOR WINGS HAVING 
MINIMUM DRAG DUE TO LIFT. Warren A. Tucker. 
December 1954. 26p. diagrs. (NACA TN 3317) 



Thickness 
(1.2.1.2.2) 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
WITH A SWEPT -BACK TAIL FROM TESTS AT 
TRANSONIC SPEEDS BY THE NACA WING-FLOW 
METHOD. John A. Zalovcik and Richard H. Sawyer. 
March 28, 1947. 30p. di^rs., photos., tab. (NACA 
RM L6K21) 

THE SUBSONIC AERODYNAMIC CHARACTERISTICS 
OF TWO DOUBLE-WEDGE AIRFOIL SECTIONS 
SUITABLE FOR SUPERSONIC FUGHT. Joseph 
Solomon and Floyd W. Henney. May 12, 1947. 33p. 
diagrs., photos. (NACA RM A6G24) 



MEASUREMENTS OF THE EFFECTS OF THICK- 
NESS RATIO AND ASPECT RATIO ON THE DRAG 
OF RECTANGULAR-PLAN-FORM AIRFOILS AT 
TRANSONIC SPEEDS. Jim Rogers Thompson and 
Charles W. Mathews. June 20, 1947. 17p. diagrs., 
photo. (NACA RM L7E08) 



APPLICATION OF ONE PART OF VON RAHMAN'S 
TWO-DIMENSIONAL TRANSONIC SIMILARITY LAW 
TO DRAG DATA OF NACA 65-SERIES WINGS. 
Kenneth B. Amer. August 24, 1948. 9p. diagrs. 
(NACA RM L8F24) 

AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBER OF 1.25 OF A 6 -PERCENT-THICK TRIAN- 
GULAR WING AND 6- AND 9-PERCENT-THICK TRI- 
ANGULAR WINGS IN COMBINATION WITH A FUSE- 
LAGE. WING ASPECT RATIO 2.31, BICONVEX AIR- 
FOIL SECTIONS. Albert W. HaU and Garland J. 
Morris. May 5, 1950. 22p. diagrs., photo., 2 tabs. 
(NACA RM L50D05) 

RESULTS OF FLIGHT TESTS TO DETERMINE THE 
ZERO-LIFT DRAG CHARACTERISTICS OF A 60° 
DELTA WING WITH NACA 65-006 AIRFOIL SEC- 
TION AND VARIOUS DOUBLE -WEDGE SECTIONS 
AT MACH NUMBERS FROM 0.7 TO 1.6. Clement J. 
Welsh. August 11, 1950. 15p. diagrs., photo. 
(NACA RM L50F01) 

DAMPING IN ROLL OF RECTANGULAR WINGS OF 
SEVERAL ASPECT RATIOS AND NACA 65A-SERIES 
AIRFOIL SECTIONS OF SEVERAL THICKNESS 
RATIOS AT TRANSONIC AND SUPERSONIC SPEEDS 
AS DETERMINED WITH ROCKET -POWERED 
MODELS. James L. Edmondson. August 24, 1950. 
16p. diagrs. (NACA RM L50E26) 

INVESTIGATION AT SUPERSONIC SPEEDS OF SOME 
OF THE FACTORS AFFECTING THE FLOW OVER A 
RECTANGULAR WING WITH SYMMETRICAL 
CIRCULAR-ARC SECTION AND 30-PERCENT- 
CHCiRD TRAILING-EDGE FLAP. K. R. Czarneckl 
and James N. Mueller. January 2, 1951. lllp. 
diagrs., photos. (NACA RM L50J18) 



PRESSURE PULSATIONS ON RIGID AIRFOILS AT 
TRANSONIC SPEEDS. Milton D. Humphreys. 
December 1951. 21p. diagrs., photos., tab. 
(NACA RM L51I12) 

THE EFFECTS ON THE AERODYNAMIC CHARAC- 
TERISTICS OF VARYING THE WING THICKNESS 
RATIO OF A TRIANGULAR WDJG-BODY fcONFIG- 
UKATION AT TRANSONIC SPEEDS FROM TESTS BY 
THE NACA WING-FLOW METHOD. Albert W. Hall 
and James M. McKay. April 1952. 27p. diagrs., 
photo., 2 tabs. (NACA RM L52B18) 

EFFECT OF THICKNESS. CAMBER, AND THICK- 
NESS DISTRIBUTION ON AIRFOIL CHARACTERIS- 
TICS AT MACH NUMBERS UP TO 1.0. Bernard N. 
Daley and Richard S. Dick. October 1952. 76p. 
photos., diagrs., tab. (NACA RM L52G31a) 



THEORETICAL STUDY OF THE TRANSONIC LIFT 
OF A DOUBLE-WEDGE PROFILE WITH DETACHED 
BOW WAVE. Walter G. Vincenti and Cleo B. 
Wagoner. (Portions of this work were reported at 
the eighth International Congress on Theoretical and 
Applied Mechanics, Istanbul, Turkey, August 20-28, 
1952). 1954. ii, 24p. diagrs., 2 tabs. (NACA 
Rept. 1180. Formerly TN 2832) 

AIRFOIL SECTION CHARACTERISTICS AT HIGH 
ANGLES OF ATTACK. Laurence K. Loftin, Jr. 
August 1954. lOp. diagrs. (NACA TN 3241) 

GENERAL THEORY OF CONICAL FLOWS AND ITS 
APPLICATION TO SUPERSONIC AERODYNAMICS. 
(La theorie generale des mouvements coniques et 
ses applications a I'aerodynamique supersonique). 
Paul Germain. PREFACE. M. J. Peres. 
January 1955. vil, 333p. diagrs. (NACA 
TM 1354. Trans, from Office National d'itudes et 
de Recherches Aeronautiques, Pub. 34, 1949) 



AERODYNAMICS 
16 WINGS (1.2) 



Thickness Distribution 
(1.2. 1.2.3) 

RESULTS OF FLIGHT TESTS TO DETERMINE THE 
ZERO-LIFT DRAG CHARACTERISTICS OF A 60° 
DELTA WING WITH NACA 65-006 AIRFOIL SEC- 
TION AND VARIOUS DOUBLE-WEDGE SECTIONS 
AT MACH NUMBERS FROM 0.7 TO 1.6. Clement J. 
Welsh. August 11, 1950. 15p. diagrs., photo. 
(NACA RM L50F01) 

UFT AND MOMENT CHARACTERISTICS AT SUB- 
SONIC MACH NUMBERS OF FOUR 10-PERCENT- 
THICK AIRFOIL SECTIONS OF VARYING TRAILING- 
EDGE THICKNESS. James L. Summers and William 
A. Page. December 20, 1950. 32p. diagrs., photos. 
(NACA RM A50J09) 

WING-FLOW INVESTIGATION OF THE CHARAC- 
TERISTICS OF SEVEN UNSWEPT, UNTAPERED 
AIRFOILS OF ASPECT RATIO 8.0. Harold L. Crane 
and James J. Adams. June 13, 1951. 54p. diagrs., 
photo. (NACA RM L51D24a) 

EFFECT OF TRAILING-EDGE THICKNESS ON LIFT 
AT SUPERSONIC VELOCITIES. Dean R. Chapman 
and Robert H. Kester. July 1952. 24p. diagrs., 
photos. (NACA RM A52D17) 

EFFECT OF THICKNESS, CAMBER, AND THICK- 
NESS DISTRIBUTION ON AIRFOIL CHARACTERIS- 
TICS AT MACH NUMBERS UP TO 1.0. Bernard N. 
Daley and Richard S. Dick. October 1952. 76p. 
photos., diagrs.. tab. (NACA RM L52G31a) 

INFLUENCE OF AIRFOIL TRAILING-EDGE ANGLE 
AND TRAILING-EDGE -THICKNESS VARIATION ON 
THE EFFECTIVENESS OF A PLAIN FLAP AT HIGH 
SUBSONIC MACH NUMBERS. Albert D. Hemenover 
and Donald J. Graham. June 1954. lOlp. diagrs., 
photos., 5 tabs. (NACA TN 3174. Formerly 
RM A51C12a) 

TABLES FOR THE COMPUTATION OF WAVE DRAG 
OF ARROW WINGS OF ARBITRARY AIRFOIL SEC- 
TION. Frederick C. Grant and Morton Cooper. 
June 1954. 9p. diagr., 28p. tabs, (in pocket) (NACA 
TN 3185) 

EXPLORATORY INVESTIGATION OF AN AIRFOIL 
WITH AREA SUCTION APPLIED TO A POROUS, 
ROUND TRAILING EDGE FITTED WITH A LIFT- 
CONTROL VANE. Robert E. Dannenberg and James 
A. Weiberg. April 1955. 55p. diagrs., photos., 
2 tabs. (NACA TN 3498) 

AERODYNAMIC CHARACTERISTICS OF SEVERAL 
6-PERCENT -THICK AIRFOILS AT ANGLES OF 
ATTACK FROM 0° TO 20° AT HIGH SUBSONIC 
SPEEDS. Bernard N. Daley and Douglas R. Lord. 
May 1955. 57p. diagrs., photos. (NACA TN 3424. 
Formerly RM L9E19) 

Inlets and Exits 



(1.2.1.2.4) 

THE USE OF SUCTION TO PREVENT SHOCK- 
INDUCED SEPARATION IN A NOZZLE. James R. 
Sterrett, Robert W. Dunning and Maurice J. Brevoort. 
January 30, 1951. 64p. diagrs., photos., 2 tabs. 
(NACA RM L50K20) 

Surface Conditions 
(1.2.1,2.5) 

A PRELIMINARY FLIGHT INVESTIGATION OF THE 
EFFECTS OF VORTEX GENERATCHIS ON SEPARA- 
TION DUE TO SHOCK. Lindsay J. Lina and Wilmer 
H. Reed, HI. November 30, 1950. 30p. diagrs., 
photos., tab. (NACA RM L50J02) 



INVESTIGATION AT SUPERSONIC SPEEDS OF SOME 
OF THE FACTORS AFFECTING THE FLOW OVER A 
RECTANGULAR WING WITH SYMMETRICAL 
CIRCULAR-ARC SECTION AND 30-PERCENT- 
CHORD TRAILING-EDGE FLAiP. K. R. Czarnecki 
and James N. MueUer. January 2, 1951. lllp. 
diagrs., photos. (NACA RM L50J18) 

INVESTIGATION AT HIGH AND LOW SUBSONIC 
MACH NUMBERS OF TWO SYMMETRICAL 6- . 
PERCENT-THICK AIRFOIL SECTIONS DESIGNED 
TO HAVE HIGH MAXIMUM LIFT COEFFICIENfS 
AT LOW SPEEDS. Nicholas J. Paradise. October 
1952. 37p. diagrs., plioto., 2 tabs. (NACA 
RM L52I02) 

IMPINGEMENT OF WATER DROPLETS ON WEDGES 
AND DOUBLE-WEDGE AIRFOILS AT SUPERSONIC 
SPEEDS. Johns. Seraflni. 1954. li, 2^. diagrs. 
(NACARept. 1159. Formerly TN 2971) 

IMPINGEMENT OF WATER DROPLETS ON NACA 
65A004 AIRFOIL AT 8° ANGLE OF ATTACK. 
Rinaldo J. Brun, Helen M. Gallagher and Dorothea 
E. Vogt. July 1954. 27p. diagrs. (NACA TN 3155) 

AIRFOIL SECTION CHARACTERISTICS AT HIGH 
ANGLES OF ATTACK. Laurence K. Loftin, Jr. 
August 1954. lOp. diagrs. (NACA TN 3241) ■ 

AERODYNAMIC CHARACTERISTICS OF NACA 0012 
AIRFOn, SECTION AT ANGLES OF ATTACK FROM 
0° TO 180°. Chris C. Critzos, Harry H. Heyson 
and Robert W. Boswinkle, Jr. January 1955. 21p. 
diagrs. (NACA TN 3361) 

A DYE-TRACER TECHNIQUE FOR EXPERIMENTAL- 
LY OBTAINING IMPINGEMENT CHARACTERISTICS 
OF ARBITRARY BODIES AND A METHOD FOR 
DETERMINING DROPLET SIZE DISTRIBUTION. 
Uwe H. von Glahn, Thomas F. Gelder and William H. 
Smyers, Jr. March 1955. 73p. diagrs., photos., 
tab. (NACA TN 3338) 



DESIGNATED PROFILES 
(1.2.1,3)' 

DRAG MEASUREMENTS OF A 34° SWEPT- 
FORWARD AND SWEPT -BACK NACA 65-009 AIR- 
FOIL OF ASPECT RATIO 2.7 AS DETERMINED BY 
FLIGHT TESTS AT SUPERSONIC SPEEDS. Sidney 
R. Alexander. February 20, 1947. lip. diagrs., 
photos. (NACA RM L6I11) 

LONGITUDINAL STABIUTY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
WITH A SWEPT -BACK TAIL FROM TESTS AT 
TRANSONIC SPEEDS BY THE NACA WING-FLOW 
METHOD. John A. Zalovcik and Richard H. Sawyer. 
March 28, 1947. 30p. diagrs., photos., tab. (NACA 
RM L6K21) 

DRAG MEASUREMENTS OF A SWEPT -BACK WING 
HAVING INVERSE TAPER AS DETERMINED BY 
FLIGHT TESTS AT SUPERSONIC SPEEDS. Sidney 
R. Alexander. April 8, 1947. 12p. diagrs., photo. 
(NACA RM L6L30) 

OBSERVATIONS ON AN AILERON-FLUTTER IN- 
STABIUTY ENCOUNTERED ON A 45° SWEPT- 
BACK WING IN TRANSONIC AND SUPERSONIC 
FLIGHT. Marvin Pitkin, William N. Gardner and 
Howard J. Curfman, Jr. April 11, 1947. 23p. 
di^rs., photos. (NACA RM L6L09) 

THE SUBSONIC AERODYNAMIC CHARACTERISTICS 
OF TWO DOUBLE-WEDGE AIRFOIL SECTIONS 
SmTABLE FOR SUPERSONIC FUGHT. Joseph 
Solomon and Floyd W. Henney. May 12, 1947. 33p. 
diagrs., photos. (NACA RM A6G24) 



AERODYNAMICS 
WINGS (1.2) 



17 



Designated Profiles - Wing Sections 
(Cont. ) 

MEASUREMENTS OF THE EFFECTS OF THICK- 
NESS RATIO AND ASPECT RATIO ON THE DRAG 
OF RECTANGDLAH-PLAN-FORM AIRFOILS AT 
TRANSONIC SPEEDS. Jim Rogers Thompson and 
Charles W. Mathews. J>me 20, 1947. 17p. diagrs., 
photo. (NACA RM L7E08) 

REDUCTION OF PROFILE DRAG AT SUPERSONIC 
VELOCITIES BY THE USE OF AIRFOIL SECTIONS 
HAVING A BLUNT TRAILING EDGE. Dean R. 
Chapman. November 1, 1949. 31p. diagrs., photo. 
(NACA RM A9H11) 

FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.6 to 1.7 TO DETERMINE DRAG AND BASE 
PRESSURES ON A BLUNT -TRAILING-EDGE AIR- 
FOIL AND DRAG OF DIAMOND AND CIRCULAR- 
ARC AIRFOILS AT ZERO LIFT. John D. Morrow 
and Ellis Katz. August 11, 1950. 25p. diagrs., 
photos. (NACA RM L50E19a) 

MEASUREMENTS OF THE EFFECT OF TRAILING- 
EDGE THICKNESS ON THE ZERO-LIFT DRAG OF 
THIN LOW-ASPECT-RATIO WINGS. John D. 
Morrow. August 14, 1950. 12p. diagrs., photo. 
(NACA RM L50F26) 

UFT AND MOMENT CHARACTERISTICS AT SUB- 
SONIC MACH NUMBERS OF FOUR 10-PERCENT- 
THICK AIRFOIL SECTIONS OF VARYING TRAILING- 
EDGE THICKNESS. James L. Summers and WilUam 
A. Page. December 20, 1950. 32p. diagrs., photos. 
(NACA RM A50J09) 

WING-FLOW INVESTIGATION OF THE CHARAC- 
TERISTICS OF SEVEN UNSWEPT, UNTAPERED 
AIRFOILS OF ASPECT RATIO 8.0. Harold L. Crane 
and James J. Adams. June 13, 1951. 54p. diagrs., 
photo. (NACA RM L51D24a) 



THE EFFECTS OF CAMBER AND LEADING-EDGE- 
FLAP DEFLECTION ON THE PRESSURE PULSA- 
TIONS ON THIN RIGID AIRFOH^S AT TRANSONIC 
SPEEDS. Milton D. Humphreys and John D. Kent. 
October 1952. 26p. diagrs., photos., tab. (NACA 
RM L52G22) 

TRANSONIC AERODYNAMIC CHARACTERISTICS 
OF AN NACA 64A006 AIRFOIL SECTION WITH A 
15 -PERCENT -CHORD LEADING-EDGE FLAP. 
Milton D. Humphreys. September 1953. 44p. 
diagrs., photos. (NACA RM L53G23) 

STUDY OF THE SUBSONIC FORCES AND MOMENTS 
ON AN INCLINED PLATE OF INFINITE SPAN. 
Bradford H. Wick. June 1954. 25d. diagrs. (NACA 
TN 3221) 

HOVERING PERFORMANCE OF A HELICOPTER 
ROTOR USING NACA 8-H-12 AIRFOIL SECTIONS. 
Robert D. Powell, Jr. August 1954. 14p. diagrs., 
photos. (NACA TN 3237) 

SECTION CHARACTERISTICS OF AN NACA 0006 
AIRFOIL WITH AREA SUCTION NEAR THE LEAD- 
ING EDGE. James A. Weiberg and Robert E. 
Dannenberg. September 1954. 47p. diagrs., photos., 
3 tabs. (NACA TN 3285) 

AERODYNAMIC CHARACTERISTICS OF NACA 0012 
AIRFOIL SECTION AT ANGLES OF ATTACK FROM 
0° TO 180°. Chris C. Critzos, Harry H. Heyson 
and Robert W. Boswinkle, Jr. January 1955. 21p. 
diagrs. (NACA TN 3361) 



HYDRODYNAMIC TARES AND INTERFERENCE 
EFFECTS FOR A 12-PERCENT -THICK SURFACE- 
PIERCING STRUT AND AN ASPECT-RATIO-0.25 
LIFTING SURFACE. John A. Ramsen and Victor L. 
Vaughan, Jr. April 1955. 20p. diagrs. (NACA 
TN 3420) 

HIGH-LIFT DEVICES 
(1.2.1.4) 

LANDING CHARACTERISTICS OF HIGH-SPEED 
WINGS. Herbert A. Wilson, Jr. and Laurence K. 
Loftin, Jr. September 21, 1948. 21p. diagrs. 
(NACA RM L8A28e) 



PRELIMINARY INVESTIGATION OF THE DELAY 
OF TURBULENT FLOW SEPARATION BY MEANS 
OF WEDGE-SHAPED BODIES. George B. 
McCuUough, Gerald E. Nltzberg and John A. Kelly. 
March 1, 1951. 28p. diagrs., photos. (NACA 
RM A50L12) 



PRESSURE DISTRIBUTION AND AERODYNAMIC 
COEFFICIENTS ASSOCIATED WITH HEAT ADDI- 
TION TO SUPERSONIC AIR STREAM ADJACENT TO 
TWO-DIMENSIONAL SUPERSONIC WING. L Irving 
Pinkel, John S. Serafini and John L. Gregg. February 
1952. 33p. diagrs., tab. (NACA RM E51K26) 



EXPERIMENTAL INVESTIGATION OF THE EF- 
FECTS OF VORTEX GENERATORS ON THE MAXI- 
MUM LIFT OF A 6-PERCENT -THICK SYMMETRI- 
CAL CIRCULAR-ARC AIRFOIL SECTION. WiUiam 
J. Bursnall. October 1952. 16p. diagrs., 2 tabs. 
(NACA RM L52G24) 

TRANSONIC AERODYNAMIC CHARACTERISTICS 
OF AN NACA 64A006 AIRFOIL SECTION WITH A 
15-PERCENT -CHORD LEADING-EDGE FLAP. 
Milton D. Humphreys. September 1953. 44p. 
diagrs., photos. (NACA RM L53G23) 

AERODYNAMIC LOADS ON A LEADING-EDGE 
FLAP AND A LEADING-EDGE SLAT ON THE 
NACA 64A010 AIRFOIL SECTION. John A. Kelly 
and George B. McCuUou^. June 1954. 33p. 
diagrs., 8 tabs. (NACA TN 3220) 

SECTION CHARACTERISTICS OF AN NACA 0006 
AIRFOIL WITH AREA SUCTION NEAR THE LEAD- 
ING EDGE. James A. Weiberg and Robert E. 
Dannenberg. September 1954. 47p. diagrs., photos., 
3 tabs. (NACA TN 3285) 



Plain Flaps 
(1.2.1.4. 1) 

AERODYNAMIC FORCES AND LOADINGS ON 
SYMMETRICAL CIRCULAR -ARC AIRFOILS WITH 
PLAIN LEADING-EDGE AND PLAIN TRAILING- 
EDGE FLAPS. Jones F. Cahill, William J. 
Underwood, Robert J. Nuber and Gall A. Cheesman. 
1953. ii, 38p. diagrs., photos., 5 tabs. (NACA Kept. 
1146. Formerly RM L6K22; RML7H04; RML50H17a) 



INFLUENCE OF AIRFOIL TRAILING-EDGE ANGLE 
AND TRAILING-EDGE -THICKNESS VARIATION ON 
THE EFFECTIVENESS OF A PLAIN FLAP AT HIGH 
SUBSONIC MACH NUMBERS. Albert D. Hemenover 
and Donald J. Graham. June 1954. lOlp. diagrs., 
photos., 5 tabs. (NACA TN 3174. Formerly 
RM A51C12a) 



AERODYNAMICS 
18 WINGS (1.2) 



Plain Flaps - Wing Sections (Cont. ) 

LIFT ON A BENT, FLAT PLATE. (Auftrieb einer 
geknlcktenebenen Platte). F. Keune. February 
1955. 15p. diagrs. (NACA TM 1340. Trans, from 
Berlcht der Aerodynamlscher Versuchsanstalt 
Gbttingen. Luftfahrtforschung, Mar. 20, 1936, 
Annual Volume, p. 85-87) 

EXPLORATORY INVESTIGATION OF AN AIRFOIL 
WITH AREA SUCTION APPLIED TO A POROUS, 
ROUND TRAILING EDGE FITTED WITH A LIFT- 
CONTROL VANE. Robert E. Dannenberg and James 
A. Welberg. April 1955. 55p. diagrs., photos., 

2 tabs. (NACA TN 3498) 

Split Flaps 
(1.2.1,4.2) 

SECTION CHARACTERBTICS OF AN NACA 0006 
AIRFOIL WITH AREA SUCTION NEAR THE LEAD- 
ING EDGE. James A. Weiberg and Robert E. 
Dannenberg. September 1954. 47p. diagrs., photos., 

3 tabs. (NACA TN 3285) 

Loading-Edge Flaps 
(1.2.1.4.4) 

THE EFFECTS OF CAMBER AND LEADING-EDGE - 
FLAP DEFLECTION ON THE PRESSURE PULSA- 
TIONS ON THIN RIGID AIRFOILS AT TRANSONIC 
SPEEDS. Milton D. Humphreys and John D. Kent. 
October 1952. 26p. diagrs., photos., tab. (NACA - 
RM L52G22) 

AERODYNAMIC FORCES AND LOADINGS ON 
SYMMETRICAL CIRCULAR -ARC AIRFOILS WITH 
PLAIN LEADING-EDGE AND PLAIN TRAILING- 
EDGE FLAPS. Jones F. CahiU, William J. 
Underwood, Robert J. Nuber and Gail A. Cheesman. 
1953. ii, 38p. diagrs., photos., 5 tabs. (NACA Rept. 
1146. Formerly RM L6K22; RML7H04; RML50H17a) 

TRANSONIC AERODYNAMIC CHARACTERISTICS 
OF AN NACA 64A006 AIRFOIL SECTION WITH A 
15-PERCENT -CHORD LEADING-EDGE FLAP. 
Milton D. Humphreys. September 1953. 44p. 
diagrs., photos. (NACA RM L53G23) 



CONTROLS 
(1.2.1.5) 

Flap Type 
(1.2.1.5.1) 

PRELIMINARY INVESTIGATION OF VARIOUS 
AILERONS ON A 42° SWEPTBACK WING FOR 
LATERAL CONTROL AT TRANSONIC SPEEDS. 
Thomas R. Turner, Vernard E. Lockwood and 
Raymond D. Vogler. September 7, 1948. 35p. 
diagrs., photo. (NACA RM L8D21) 

INVESTIGATION AT SUPERSONIC SPEEDS OF SOME 
OF THE FACTORS AFFECTING THE FLOW OVER A 
RECTANGULAR WING WITH SYMMETRICAL 
CIRCULAR-ARC SECTION AND 30-PERCENT- 
CHORD TRAILING-EDGE FLAP. K. R. Czamecki 
and James N. MueUer. January 2, 1951. lllp. 
diagrs., photos. (NACA RM L50J18) 



INFLUENCE OF AIRFOIL TRAILING-EDGE ANGLE 
AND TRAILING-EDGE-THICKNESS VARIATION ON 
THE EFFECTIVENESS OF A PLAIN FLAP AT HIGH 
SUBSONIC MACH NUMBERS. Albert D. Hemenover 
and Donald J. Graham. June 1954. lOlp. diagrs., 
photos., 5 tabs. (NACA TN 3174. Formerly 
RM A51C12a) 



EXPLORATORY INVESTIGATION OF AN AIRFOIL 
WITH AREA SUCTION APPLIED TO A POROUS, 
ROiraO TRAILING EDGE FITTED WITH A LIFT- 
CONTROL VANE. Robert E. Dannenberg and James 
A. Weiberg. April 1955. 55p. diagrs., photos., 
2 tabs. (NACA TN 3498) 

Spoilers 



(1.2.1.5.2) 

PRELIMINARY INVESTIGATION OF VARIOUS 
AILERONS ON A 42° SWEPTBACK WING FOR 
LATERAL CONTROL AT TRANSONIC SPEEDS. 
Thomas R. Turner, Vernard E. Lockwood and 
Raymond D. Vogler. September 7, 1948. 35p. 
diagrs., photo. (NACA RM L8D21) 



BOUNDARY LAYER 
(1.2.1.6) 

INVESTIGATION AT MACH NUMBER 1.62 OF THE 
PRESSURE DISTRIBUTION OVER A RECTANGULAR 
WING WITH SYMMETRICAL CIRCULAR-ARC SEC- 
TION AND 30-PERCENT -CHORD TRAILING-EDGE 
FLAP. K. R. Czamecki and James N. MueUer. 
January 25, 1950. Sip. diagrs., photos. (NACA 
RM L9J05) 

PRESSURE MEASUREMENTS AT SUPERSONIC 
SPEEDS ON A SECTION OF A RECTANGULAR 
WING HAVING AN NACA 65-009 PROFILE. , Robert 
W. Rainey. March 10, 1950. 31p. diagrs., photos., 
tab. (NACA RM L9L16) 

A PRELIMINARY FUGHT INVESTIGATION OF THE 
EFFECTS OF VORTEX GENERAT(aiS ON SEPARA- 
TION DUE TO SHOCK. Lindsay J. Lina and Wilmer 
H. Reed, m. November 30, 1950. 30p. diagrs., 
photos., tab. (NACA RM L50J02) 

EXPERIMENTAL INVESTIGATION OF THE EF- 
FECTS OF VORTEX GENERATORS ON THE MAXI- 
MUM LIFT OF A 6-PERCENT -THICK SYMMETRI- 
CAL CIRCULAR -ARC AIRFOIL SECTION. WiUiam 
J. Bursnall. October 1952. 16p. diagrs., 2 tabs. 
(NACA RM L52G24) 

STUDY OF THE MOMENTUM DISTRIBUTION OF 
TOTBULENT BOUNDARY LAYERS IN ADVERSE 
PRESSURE GRADIENTS. Virgil A. Sandborn and 
Raymond J. Slogar. January 1955. 79p. diagrs., 
photos. (NACA TN 3264) 

EXPERIMENTS ON TURBULENT FLOW THROUGH 
CHANNELS HAVING POROUS ROUGH SURFACES 
WITH OR WITHOUT AIR INJECTION. E. R. G. 
Eckert, Anthony J. Diaguila and Patrick L. 
Donou^e. February 1955. 45p. diagrs., photos., 
tab. (NACA TN 3339) 



Characteristic s 
(1.2.1.6.1) 

PRELIMINARY INVESTIGATION OF THE TRAN- 
SONIC CHARACTERISTICS OF AN NACA SUB- 
MERGED INLET. John A. Axelson and Robert A. 
Taylor. June 5, 1950. 44p. diagrs., photos. 
(NACA RM A50C13) 

INVESTIGATION AT SUPERSONIC SPEEDS OF SOME 
OF THE FACTORS AFFECTING THE FLOW OVER A 
RECTANGULAR WING WITH SYMMETRICAL 
CmCULAH-ARC SECTION AND 30-PERCENT- 
CHORD TRAILING-EDGE FLAP. K. R. Czamecki 
and James N. Mueller. January 2, 1951. lllp. 
diagrs., photos. (NACA RM L50J18) 



AERODYNAMICS 

WINGS (1.2)19 



Wing Sections 



Characteristics 
(Cont. ) 

PREUMINARy INVESTIGATION OF THE DELAY 
OF TURBULENT FLOW SEPARATION BY MEANS 
OF WEDGE-SHAPED BODIES. George B. 
McCuUough, Gerald E. Kitzberg and John A. Kelly. 
March 1, 1951. 28p. diagrs., photos. (NACA 
RM A50L12) 

SECTION CHARACTERISTICS OF AN NACA 0006 
AIRFOIL WITH AREA SUCTION NEAR THE LEAD- 
ING EDGE. James A. Welberg and Robert E. 
Dannenberg. September 1954. 41p. diagrs., photos., 
3 tabs. (NACA TN 3285) 

Control 
(1.2.1.6.2) 

INVESTIGATION OF A SIMPLE DEVICE FOR PRE- 
VENTING SEPARATION DUE TO SHOCK AND 
BOUNDARY-LAYER INTERACTION. Coleman duP. 
Donaldson. November 29, 1950. 34p. diagrs., 
photos. (NACA RM L50B02a) 

THE USE OF SUCTION TO PREVENT SHOCK- 
INDUCED SEPARATION IN A NOZZLE. James R. 
Sterrett, Robert W. Dunning and Maurice J. Brevoort. 
January 30, 1951. 64p. diagrs., photos., 2 tabs. 
(NACA RM L50K20) 



PRELIMINARY INVESTIGATION OF THE DELAY 
OF TURBULENT FLOW SEPARATION BY MEANS 
OF WEDGE-SHAPED BODIES. George B. 
McCuUough, Gerald E. Nitzberg and John A. Kelly. 
March 1, 1951. 28p. diagrs., photos. (NACA 
RM A50L12) 

SECTION CHARACTERISTICS OF AN NACA 0006 
AIRFOIL WITH AREA SUCTION NEAR THE LEAD- 
ING EDGE. James A. Welberg and Robert E. 
Dannenberg. September 1954. 47p. diagrs., photos., 
3 tabs. (NACA TN 3285) 

A FIBROUS-GLASS COMPACT AS A PERMEABLE 
MATERIAL FOR BOUNDARY -LAYER-CONTROL 
APPLICATIONS USING AREA SUCTION. Robert E. 
Dannenberg, James A. Weiberg and Bruno J. 
Gambucci. January 1955. 20p. diagrs., photos., 
2 tabs. (NACA TN 3388) 

EXPLORATORY INVESTIGATION OF AN AIRFOIL 
WITH AREA SUCTION APPLIED TO A POROUS, 
ROUND TRAILING EDGE FITTED WITH A LIFT- 
CONTROL VANE. Robert E. Dannenberg and James 
A. Weiberg. April 1955. 55p. diagrs., photos., 
2 tabs. (NACA TN 3498) 



EFFECT OF A DISCONTINUITY ON TURBULENT 
BOUNDARY-LAYER-THICKNESS PARAMETERS 
WITH APPLICATION TO SHOCK-INDUCED SEPARA- 
TION. Eli Reshotko and Maurice Tucker. May 1955. 
21p. diagrs. (NACA TN 3454) 



REYNOLDS NUMBER EFFECTS 
(1.2.1.7) 



INVESTIGATION AT MACH NUMBER 1.62 OF THE 
PRESSURE DISTRIBUTION OVER A RECTANGULAR 
WING WITH SYMMETRICAL CIRCULAR-ARC SEC- 
TION AND 30-PERCENT -CHORD TRAILING-EDGE 
FLAP. K. R. Czarnecki and James N. Mueller. 
January 25, 1950. 81p. diagrs., photos. (NACA 
RM L9J05) 



EXPLORATORY INVESTIGATION AT HIGH AND 
LOW SUBSONIC MACH NUMBERS OF TWO EXPERI- 
MENTAL 6-PERCENT-THICK AIRFOIL SECTIONS 
DESIGNED TO HAVE HIGH MAXIMUM LIFT COEF- 
FICIENTS. Laurence K. Loftin, Jr. and Albert E. 
von Doenhoff . December 1951. 48p. diagrs., photo., 
2 tabs. (NACA RM L51F06) 

investigation at high and low subsonic 
m;.ch numbers of two symmetrical 6- 
percent-thick airfoil sections designed 
to have high maximum lift coefficients 

AT LOW SPEEDS. Nicholas J. Paradiso. October 

1952. 37p. diagrs., photo., 2 tabs. (NACA 
RM L52I02) 

AERODYNAMIC FORCES AND LOADINGS ON 
SYMMETRICAL CIRCULAR -ARC AIRFOILS WITH 
PLAIN LEADING-EDGE AND PLAIN TRAILING- 
EDGE FLAPS. Jones F. CahlU, William J. 
Underwood, Robert J. Nuber and Gail A. Cheesman. 

1953. ii, 38p. diagrs., photos., 5 tabs. (NACA Rept. 
1146. Formerly RML6K22; RML7H04; RML50Hna) 

STUDY OF THE SUBSONIC FORCES AND MOMENTS 
ON AN INCLINED PLATE OF INFINITE SPAN. 
Bradford H. Wick. June 1954. 25p. diagrs. (NACA 
TN 3221) 

AIRFOIL SECTION CHARACTERISTICS AT HIGH 
ANGLES OF ATTACK. Laurence K. Loftin, Jr. 
August 1954. lOp. diagrs. (NACA TN 3241) 

AERODYNAMIC CHARACTERISTICS OF THE NACA 
64-010 AND 0010-1.10 40/1.051 AIRFOIL SECTIONS 
AT MACH NUMBERS FROM 0.30 TO 0.85 AND 
REYNOLDS NUMBERS FROM 4.0 x 10° TO 8.0 X 10°. 
Laurence K. Loftin, Jr. August 1954. 17p. diagrs., 
tab. (NACA TN 3244) 

AERODYNAMIC CHARACTERISTICS OF NACA 0012 
AIRFOIL SECTION AT ANGLES OF ATTACK FROM 
0° TO 180°. Chris C. Critzos, Harry H. Heyson 
and Robert W. Boswinkle, Jr. January 1955. 21p. 
diagrs. (NACA TN 3361) 

HYDRODYNAMIC TARES AND INTERFERENCE 
EFFECTS FOR A 12-PERCENT-THICK SURFACE- 
PIERCING STRUT AND AN ASPECT-RATIO-0.25 
LIFTING SURFACE. John A. Ramsen and Victor L. 
Vaughan, Jr. AprU 1955. 20p. diagrs. (NACA 
TN 3420) 

THE SUBSONIC AERODYNAMIC CHARACTERISTICS 
OF TWO DOUBLE-WEDGE AIRFOIL SECTIONS 
SUITABLE FOR SUPERSONIC FLIGHT. Joseph 
Solomon and Floyd W. Henney. May 12, 1947. 33p. 
diagrs., photos. (NACA RM A6G24) 

MACH NUMBER EFFECTS 
(1.2.1.8) 

APPLICATION OF ONE PART OF VON KARMAN'S 
TWO-DIMENSIONAL TRANSONIC SIMILARITY LAW 
TO DRAG DATA OF NACA 65 -SERIES WINGS. 
Kenneth B. Amer. August 24, 1948. 9p. diagrs. 
(NACA RM L8F24) 

PRELIMINARY INVESTIGATION OF VARIOUS 
AILERONS ON A 42° SWEPTBACK WING FOR 
LATERAL CONTROL AT TRANSONIC SPEEDS. 
Thomas R. Turner, Vernard E. Lockwood and 
Raymond D. Vogler. September 7, 1948. 35p. 
diagrs., photo. (NACA RM L8D21) 

EXPERIMENTAL PRESSURE DISTRIBUTIONS OVER 
WING TIPS AT MACH NUMBER 1.9. I - WING TIP 
WITH SUBSONIC LEADING EDGE. James M. 
Jagger and Harold Mirels. January 27, 1949. 28p. 
diagrs.. photo. (NACA RM E8K26) 



20 



AERODYNAMICS 
WINGS (1.2) 



Mach Number Effect - Wing 
Sections (Cont. ) 

PRESSURE -DISTRIBUTION DATA FOR THE NACA 
64i-012 AND 641A012 AIRFOILS AT HIGH SUBSONIC 
MACH NUMBERS. Milton D. Humphreys. May 6, 
1949. 37p- photos. , diagrs. , 8 tabs. (NACA 
RM L9C18) 



EXPERIMENTAL PRESSURE DISTRIBUTIONS OVER 
WING TIPS AT MACH NUMBER 1.9. H - WING TIP 
WITH SUBSONIC TRAILING EDGE. Harold Mirels 
and James M. Jagger. December 21, 1949. 23p. 
diagrs., photo. (NACA RM E9I22a) 

PRESSURE MEASUREMENTS AT SUPERSONIC 
SPEEDS ON A SECTION OF A RECTANGULAR 
WING HAVING AN NACA 65-009 PROFILE. Robert 
W. Rainey. March 10, 1950. 31p. diagrs., photos., 
tab. (NACA RM L9L16) 

INVESTIGATION OF A SIMPLE DEVICE FOR PRE- 
VENTING SEPARATION DUE TO SHOCK AND 
BOUNDARY-LAYER INTERACTION. Coleman duP. 
Donaldson. November 29, 1950. 34p. diagrs., 
photos. (NACA RM L5OB02a) 



A PRELIMINARY FLIGHT INVESTIGATION OF THE 
EFFECTS OF VORTEX GENERATORS ON SEPARA- 
TION DUE TO SHOCK. Lindsay J. Llna and Wllmer 
H. Reed, HI. November 30, 1950. 30p. diagrs., 
photos., tab. (NACA RM L50J02) 



LIFT AND MOMENT CHARACTERISTICS AT SUB- 
SONIC MACH NUMBERS OF FOUR 10-PERCENT- 
THICK AIRFOIL SECTIONS OF VARYING TRAILING- 
EDGE THICKNESS. James L. Summers and William 
A. Page. December 20, 1950. 32p. diagrs., photos. 
(NACA I«*J A50J09) 



INVESTIGATION AT SUPERSONIC SPEEDS OF SOME 
OF THE FACTORS AFFECTING THE FLOW OVER A 
RECTANGULAR WING WITH SYMMETRICAL 
CIRCULAR-ARC SECTION AND 30-PERCENT- 
CHORD TRAILING-EDGE FLAP. K. R. Czarneckl 
and James N. Mueller. January 2, 1951. lllp. 
diagrs., photos. (NACA RM L50J18) 



THE USE OF SUCTION TO PREVENT SHOCK- 
INDUCED SEPARATION IN A NOZZLE. James R. 
Sterrett, Robert W. Dunning and Maurice J. Brevoort. 
January 30, 1951. 64p. diagrs., photos., 2 tabs. 
(NACA RM L50K20) 



WING-FLOW INVESTIGATION OF THE CHARAC- 
TERISTICS OF SEVEN UNSWEPT, UNTAPERED 
AIRFOILS OF ASPECT RATIO 8.0. Harold L. Crane 
and James J. Adams. June 13, 1951. 54p. diagrs., 
photo. (NACA RM L51D24a) 

MEASUREMENTS IN FLIGHT OF THE LONGITUDI- 
NAL CHARACTERISTICS OF TWO JET AIRCRAFT, 
ONE WITH A DIVING TENDENCY AND THE OTHER 
WITH A CLIMBING TENDENCY AT HIGH MACH 
NUMBERS. Seth B. Anderson. October 1951. 18p. 
diagrs., photos., 2 tabs. (NACA RM A51E14) 

EXPLORATORY INVESTIGATION AT HIGH AND 
LOW SUBSONIC MACH NUMBERS OF TWO EXPERI- 
MENTAL 6-PERCENT-THICK AIRFOIL SECTIONS 
DESIGNED TO HAVE HIGH MAXIMUM LIFT COEF- 
FICIENTS. Laurence K. Lottin, Jr. and Albert E. 
von Doenhoff. December 1951. 48p. diagrs., photo., 
2 tabs. (NACA RM L51F06) 



THE EFFECTS OF CAMBER AND LEADING-EDGE - 
FLAP DEFLECTION ON THE PRESSURE PULSA- 
TIONS ON THIN RIGO) AIRFOILS AT TRANSONIC 
SPEEDS. Milton D. Humphreys and John D. Kent. 
October 1952. 26p. diagrs., photos., tab. (NACA 
RM L52G22) 

EFFECT OF THICKNESS, CAMBER, AND THICK- 
NESS DISTRIBUTION ON AIRFOIL CHARACTERIS- 
TICS AT MACH NUMBERS UP TO 1.0. Bernard N. 
Daley and Richard S. Dick. October 1952. 76p. 
photos., diagrs., tab. (NACA RM L52G3 la) 

INVESTIGATION AT HIGH AND LOW SUBSONIC 
MACH NUMBERS OF TWO SYMMETRICAL 6- 
PERCENT-THICK AIRFOIL SECTIONS DESIGNED 
TO HAVE HIGH MAXIMUM LIFT COEFFICIENTS 
AT LOW SPEEDS. Nicholas J. Paradise. October 

1952. 37p. diagrs., photo., 2 tabs. (NACA 
RM L52I02) 

MEASUREMENTS OF FLUCTUATING PRESSURES 
ON A 1/4-SCALE MODEL OF THE X-1 AIRPLANE 
WITH A 10-PERCENT -THICK WING IN THE 
LANGLEY 16-FOOT TRANSONIC TUNNEL. 
Louis W. Habel and Seymour Steinberg. January 

1953. 29p. diagrs., photos. (NACA RM L52J31) 

TRANSONIC AERODYNAMIC CHARACTERISTICS 
OF AN NACA 64A006 AIRFOIL SECTION WITH A 
15-PERCENT -CHORD LEADING-EDGE FLAP. 
Milton D. Humphreys. September 1953. 44p. 
diagrs., photos. (NACA RM L53G23) 



THEORETICAL STUDY OF THE TRANSONIC LIFT 
OF A DOUBLE -WEDGE PROFILE WITH DETACHED 
BOW WAVE. Walter G. Vlncentl and Cleo B. 
Wagoner. (Portions of this work were reported at 
the eighth International Congress on Theoretical and 
Applied Mechanics, Istanbul, Turkey, August 20-28, 
1952). 1954. li, 24p. diagrs., 2 tabs. (NACA 
Rept. 1180. Formerly TN 2832) 

AN EXPERIMENTAL STUDY OF THE LIFT AND 
PRESSURE DISTRIBUTION ON A DOUBLE -WEDGE 
PROFILE AT MACH NUMBERS NEAR SHOCK 
ATTACHMENT. Walter G. Vlncentl, Duane W. Dugan 
and E. Ray Phelps. July 1954. 43p. diagrs. 
(NACA TN 3225) 

AIRFOIL SECTION CHARACTERISTICS AT HIGH 
ANGLES OF ATTACK. Laurence K. Loftln, Jr. 
August 1954. lOp. diagrs. (NACA TN 3241) 

AERODYNAMIC CHARACTERISTICS OF THE NACA 
64-010 AND 0010-1.10 40/1.051 AIRFOIL SECTIONS 
AT MACH NUMBERS FROM 0.30 TO 0.85 AND 
REYNOLDS NUMBERS FROM 4.0 x 10° TO 8.0 x 10°. 
Laurence K. Loftln, Jr. August 1954. 17p. diagrs., 
tab. (NACA TN 3244) 

AN INVESTIGATION OF A LIFTING 10-PERCENT- 
THICK SYMMETRICAL DOUBLE-WEDGE AIRFOIL 
AT MACH NUMBERS UP TO 1. Milton D. 
Humphreys. November 1954. 35p. diagrs., photos., 
tab. (NACA TN 3306) 

SECOND -ORDER SUBSONIC AIRFOIL -SECTION 
THEORY AND ITS PRACTICAL APPLICATION. 
Milton D. Van Dyke. March 1955. 50p. diagrs., 
5 tabs. (NACA TN 3390) 

AERODYNAMIC CHARACTERISTICS OF SEVERAL 
6-PERCENT-THICK AIRFOILS AT ANGLES OF 
ATTACK FROM 0° TO 20° AT HIGH SUBSONIC 
SPEEDS. Bernard N. Daley and Douglas R. Lord. 
May. 1955. 57p. diagrs., photos. (NACA TN 3424. 
Formerly RM L9E19) 



^ WAKE 
a. 2. 1.9) 

AEROD-XNAMIC INVESTIGATION AT MACH NUM- 
BER 1.92 OF A RFCTANGULAR WING AND TAIL 
AND BODY CONFIGURATION AND ITS COMPO- 
NENTS.; Macon C. EJlis, Jr. anACarl E. Grigsby, 
March 1, 1950. 96p. diagrs., photos., 4 tabs. 
(NACA RM L9L28a) 

INVESTIGATION OF A SIMPLE DEVICE FOR PRE- 
VENTING SEPARATION DUE TO SHOCK AND 
BOUNDARY-LATTER INTERACTION. Coleman duP. 
Donaldson. November 29, 1950. 34p. diagrs., 
photos. (NACA RML50B02a) 

UFT AND MOMENT CHARACTERISTICS AT SUB- 
SONIC MACH NUMBERS OF FOUR 10-PERCENT- 
THICK AIRFOIL SECTIONS OF VARYING TRAILING- 
EDGE THICKNESS. James L. Summers and William 
A. Page. December 20, 1950. 32p. diagrs., photos. 
(NACA RM A50J09) 

PRELIMINARY INVESTIGATION OF THE PRESSURE 
FLUCTUATIONS IN THE WAKES OF TWO- 
DIMENSIONAL WINGS AT LOW ANGLES OF AT- 
TACK. Robert M. Sorenson, John A. Wyss and 
James C. Kyle. October 1951. 58p. diagrs.. 
photos. (NACA RM A51G10) 

CORRELATION OF BUFFET BOUNDARIES PRE- 
DICTED FROM WIND-TUNNEL TESTS WITH THOSE 
MEASURED DURING FLIGHT TESTS ON THE F8F-1 
AND X-1 AIRPLANES - TRANSONIC-BUMP METH- 
OD. Andrew Martin and James F. Reed. 
December 1952. 22p. diagrs., photos., tab. 
(NACA RM A52J17) 

STUDY OF THE SUBSONIC FORCES AND MOMENTS 
ON AN INCLINED PLATE OF INFINITE SPAN. 
Bradford H. Wick. June 1954. 25p. diagrs. (NACA 
TN 3221) 



COMPLETE WINGS 
(1.2.2) 



WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 1.53 OF AN AIRPLANE WITH A TRIANGU- 
LAR WING. Richard Scherrer and William R. 
Wimbrow. January 23, 1948. 74p. diagrs., 
photos., 2 tabs. (NACA RM A7J05) 

FLIGHT TESTS AT SUPERSONIC SPEEDS TO 
DETERMINE THE EFFECT OF TAPER ON THE 
ZERO-UFT DRAG OF SWEPTBACK LOW-ASPECT- 
RATIO WINGS. Murray Pittel. September 5, 1950. 
23p. diagrs., photos. (NACA RM L50F30a) 

AN EXPERIMENTAL STUDY OF MODERATE AND 
HIGH SUBSONIC SPEEDS OF THE FLOW OVER AN 
UNSWEPT WING IN CONJUNCTION WITH A FUSE- 
LAGE. Richard T. Whltcomb. June 18, 1951. 35p. 
diagrs., photos. (NACA RM L50L07) 

THE EFFECTS AT TRANSONIC SPEEDS OF THICK- 
ENING THE TRAILING EDGE OF A WING WITH A 
4-PERCENT -THICK CIRCULAR-ARC AIRFOIL. . 
Joseph W. Cleary and George L. Stevens. December 
1951. 43p. diagrs., photo. (NACA RM A51J11) 



FORCE TESTS OF THREE THIN WINGS OF MOD- 
ERATELY LOW ASPECT RATIO AT HIGH SUB- 
SONIC MACH NUMBERS. Gareth H. Jordan. 
October 1952. 22p. diagrs. (NACA RM L52I08) 



AERODYNAMICS 

WINGS <1. 2) 2 1 

WING THEORY 
(1.2.2.1) 



A TORSIONAL STIFFNESS CRITERION FOR PRE- 
VENTING FLUTTER OF WINCS OF SUPERSONIC 
MISSILES. Bernard Budiansky, Joseph N. Kotanchik 
and Patrick T. Chiarito. August 28, 1947. 14p. 
diagrs., tab. (NACA RM L7G02) 

INVESTIGATION AT SUPERSONIC SPEED (M = 1. 53) 
OF THE PRESSURE DISTRIBUTION OVER A 63° 
SWEPT AIRFOIL OF BICONVEX SECTION AT 
ZERO LIFT. Charles W. Frick and John W. Boyd. 
June 10, 1948. 33p. diagrs. , photos. (NACA 
RM A8C22) 

INVESTIGATION AT SUPHISONIC SPEED (M = 1.53) 
OF THE PRESSURE DISTREBimON OVER A 63° 
SWEPT AIRFOIL OF BICONVEX SECTION AT SEV- 
ERAL ANGLES OF ATTACK. John W. Boyd, Elliott 
D. Katzen and Charles W. Fri(&. S^ember 24, 
1948. 41p. diagrs., photos., tab. (NACA RM A8F22) 

ESTIMATION OF LIFT AND DRAG OF AIRFOILS AT 
NEAR SONIC SPEEDS AND IN THE PRESENCE OF 
DETACHED SHOCK WAVES. John P. Mayer. 
February 23, 1949. 23p. diagrs. (NACA RM L8L07) 

FLIGHT TESTS AT SUPERSONIC SPEEDS TO 
DETERMINE THE EFFECT OF TAPER ON THE 
ZERO-LIFT DRAG OF SWEPTBACK LOW-ASPECT- 
RATIO WINGS. Murray Pittel. September 5, 1950. 
23p. diagrs., photos. (NACA RM L50F30a) 

AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBER OF 1.38 OF FOUR WDJGS OF ASPECT 
RATIO 4 HAVING QUARTER-CHORD SWEEJP 
ANGLES OF 0°, 35°, 45°, AND 60°. WUliam B. 
Kemp, Jr., Kenneth W. Goodson and Robert A. Booth. 
October 10, 1950. 41p. diagrs., photos., tab. 
(NACA RM L50G14) 

A METHOD FOR THE DESIGN OF SWEPTBACK 
WINGS WARPED TO PRODUCE SPECIFIED FUGHT 
CHARACTERISTICS AT SUPERSONIC SPEEDS. 
Warren A. Tucker. September 1951. 52p. diagrs., 
2 tabs. (NACA RM L51F08) 

A CORRELATION OF EXPERIMENTAL ZERO-LIFT 
DRAG OF RECTANGULAR WINGS WITH SYMMET- 
RICAL NACA 85 -SERIES AIRFOIL SECTIONS BY 
MEANS OF THE TRANSONIC SIMILARITY LAW 
FOR WDJGS OF FINITE ASPECT RATIO. Edward 
C. B. Danforth. September 1951. 20p. diagrs. 
(NACA RM L51G20) 

A CORRELATION BY MEANS OF THE TRANSONIC 
SIMILARITY RULES OF THE EXPERIMENTALLY 
DETERMINED CHARACTERISTICS OF 22 RECTAN- 
GULAR WINGS OF SYMMETRICAL PROFILE. 
John B. McDevltt. February 1952. 60p. diagrs., 
3 tabs. (NACA RM A51L17b) 

AN ANALYSIS OF ESTIMATED AND EXPERIMENT- 
AL TRA!«ONIC DOWNWASH CHARACTERISTICS 
AS AFFECTED BY PLAN FORM AND THICKNESS 
FOR WING AND WING-FUSELAGE CONFIGURA- 
TIONS. Joseph Weil, George S. Campbell and 
Margaret S. Diederich. November 1952. 92p. 
diagrs. , 2 tabs. (NACA RM L52I22) 

A VECTOR STUDY OF LINEARIZED SUPERSONIC 
FLOW APPLICATIONS TO NONPLANAR 
PROBLEMS. John C. Martin. 1953. 11, 34p. 
diagrs., tab. (NACA Rept. 1143. Formerly 
TN 2641) 

ON THE APPLICATION OF TRANSONIC SIMILARITY 
RULES TO WINGS OF FINITE SPAN. John R. 
Spreiter. 1953. ii, 21p. diagrs. (NACA Rept. 1153. 
Formerly TN 2726) 



22 



AERODYNAMICS 
WINGS (1.2) 



Complete Wings 



Theory 
(Cont. ) 

A CORRELATION BY MEANS OF TRANSONIC 
SMILAHITY RULES OF THE EXPERIMENTALLY 
DETERMINED CHARACTERETICS OF 18 CAM- 
BERED VWNGS OF RECTANGULAR PLAN FORM. 
John B. McDevitt. September 1953. 57p. diagrs. 
(NACA RM A53G31) 

METHOD FOR CALCULATING THE ROLLING AND 
YAWING MOMENTS DUE TO ROLLING FOR UN- 
SWEPT WINGS WITH OR WITHOUT FLAPS OR 
AILERONS BY USE OF NONLINEAR SECTION LIFT 
DATA. Albert P. Martina. 1954. ii, 16p. diagrs., 
U tabs. (NACA Rept. 1167. Formerly TN 2937) 

THE CALCULATION OF PRESSURE ON SLENDER 
AIRPLANES IN SUBSONIC AND SUPERSONIC FLOW. 
Max. A. Heaslet and Harvard Lomax. 1954. ii. 
lip. diagrs. (NACA Rept. 1185. Formerly TN 2900) 

TABLES FOR THE COMPUTATION OF WAVE DRAG 
OF ARROW WINGS OF ARBITRARY AIRFOIL SEC- 
TION. Frederick C. Grant and Morton Cooper. 
June 1954. 9p. diagr., 28p. tabs, (in pocket) (NACA 
TN 3185) 

LIFT AND PITCHING MOMENT AT SUPERSONIC 
SPEEDS DUE TO CONSTANT VERTICAL ACCELER- 
ATION FOR THIN SWEPTBACK TAPERED WINGS 
WITH STREAMWISE TIPS. SUPERSONIC LEADING 
AND TRAILING EDGES. Isabella J. Cole and 
Kenneth Margolis. July 1954. 67p. diagrs., 4 tabs. 
(NACA TN 3196) 

THEORETICAL INVESTIGATION OF THE EFFECTS 
UPON UFT OF A GAP BETWEEN WING AND BODY 
OF A SLENDER WING-BODY COMBINATION. Duane 
W. Dugan and Katsumi Hlkido. August 1954. 41p. 
diagrs. (NACA TN 3224) 

ON THE DETERMINATION OF CERTAIN BASIC 
TYPES OF SUPEHSOKIC FLOW FIELDS. (Sulla 
determinazione di alcuni tipi dl campi di corrente 
ipersonora). Carlo Ferrari. November 1954. 17p. 
diagrs. (NACA TM 1381. Trans, from Rendicontl 
delta R. Accademie Nazionale del Llncel, Series 8, 
V. 7, no. 6, Dec. 1949) 

AERODYNAMIC FORCES, MOMENTS, AND STA- 
BILITY DERIVATIVES FOR SLENDER BODIES OF 
GENERAL CROSS SECTION. Alvin H. Sacks. 
November 1954.(1), 74p. diagrs., 2 tabs. (NACA 
TN 3283) 

GENERALIZED INDICIAL FORCES ON DEFORMING 
RECTANGULAR WINGS IN SUPERSONIC FLIGHT. 
Harvard Lomax, Franklyn B. Fuller and Loma Sluder. 
November 1954. 74p. diagrs., tab. (NACA TN 3286) 

SUBSONIC EDGES IN THIN-WING AND SLENDER- 
BODY THEORY. Milton D. Van Dyke. November 
1954. 26p. diagrs. (NACA TN 3343) 

GENERAL THEORY OF CONICAL FLOWS AND ITS 
APPLICATION TO SUPERSONIC AERODYNAMICS. 
(La theorie generate des mouvements coniques et 
ses applications a I'aerodynamique supersonique). 
Paul Germain. PREFACE. M. J. Peres. 
January 1955. vii, 333p. diagrs. (NACA 
TM 1354. Trans, from Office National d'^tudes et 
de Recherches Aeronautiques, Pub. 34, 1949) 

DESCRIPTION AND ANALYSIS OF A ROCKET- 
VEHICLE EXPERIMENT ON FLUTTER INVOLVING 
WING DEFORMATION AND BODY MOTIONS. H. J. 
Cunningham and R. R. Lundstrom. January 1955. 
26p. diagrs., photos., 2 tabs. (NACA TN 3311. 
Formerly RM L50I29) 



A NOTE ON THE DRAG DUE TO UFT OF REC- 
TANGULAR WINGS OF LOW ASPECT RATIO. 
Edward C. Polhamus. January 1955. 24p. diagrs. 
(NACA TN 3324) 

ON SLENDER DELTA WINGS WITH LEADING-EDGE 
SEPARATION. Clinton E. Brown and William H. 
Michael, Jr. April 1955. 27p. diagrs. (NACA 
TN 3430) 

THE ZERO-UFT WAVE DRAG OF A PARTICULAR 
FAMILY OF UNSWEPT, TAPERED WINGS WITH 
LINEARLY VARYING THICKNESS RATIO. Arthur 
Henderson, Jr. and Julia M. Goodwin. May 1955. 
28p. diagrs. (NACA TN 3418) 



WING VARIABLES 
(1.2.2.2) 

INVESTIGATION AT SUPERSONIC SPEED (M = 1. 53) 
OF THE PRESSURE DISTRIBUTION OVER A 63° 
SWEPT AIRFOIL OF BICONVEX SECTION AT 
ZERO LIFT. Charles W. Frlck and John W. Boyd. 
June 10, 1948. 33p. diagrs. , photos. (NACA 
RM A8C22) 

INVESTIGATION AT SUPERSONIC SPEED (M = 1.53) 
OF THE PRESSURE DBTRIBUTION OVER A 63° 
SWEPT AIRFOIL OF BICONVEX SECTION AT SEV- 
ERAL ANGLES OF ATTACK. John W. Boyd, EUlott 
D. Katzen and Charles W. Frick. September 24, 
1948. 41p. diagrs., photos., tab. (NACA RM A8F22) 

AERODYNAMIC CHARACTERJBTICS AT SUBSONIC 
AND SUPERSONIC MACH NUMBERS OF A THIN 
TRIANGULAR WING OF ASPECT RATIO 2. I - 
MAXIMUM THICKNESS AT 20 PERCENT OF THE 
CHORD. Robert E. Berggren and James L. 
Summers. November 19, 1948. 41p. diagrs., photos. 
(NACA RM A8I16) 

AERODYNAMIC CHARACTERBTICS AT SUBSONIC 
AND SUPERSONIC MACH NUMBERS OF A THIN 
TRIANGULAR WING OF ASPECT RATIO 2. H - 
MAXIMUM THICKNESS AT MIDCHORD. Harold 3. 
Walker and Robert E. Berggren. December 3, 1948. 
41p. diagrs., photos. (NACA RM A8I20) 

EFFECT OF WING SWEEP, TAPER, AND THICK- 
NESS RATIO ON THE TRANSONIC DRAG CHARAC- 
TERISTICS OF WING-BODY COMBINATIONS. Jim 
Rogers Thompson and Charles W. Mathews. 
December 31, 1948. 29p. diagrs., photos., 2 tabs. 
(NACA RM L8K01) 

INVESTIGATIONS AT SUPERSONIC SPEEDS OF 22 
TRIANGULAR WINGS REPRESENTING TWO AIR- 
FOIL SECTIONS FOR EACH OF 11 APEX ANGLES. 
Eugene S. Love. May 10, 1949. lOOp. diagrs., 
photos., 3 tabs. (NACA RM L9D07) 

A FREE-FLIGHT TECHNIQUE FOR MEASURING 
DAMPING IN ROLL BY USE OF ROCKET-POWERED 
MODEI5 AND SOME INITIAL RESULTS FOR 
RECTANGULAR WINGS. James L. Edmondson and 
E. Claude Sanders, Jr. December 20, 1949. 25p. 
diagrs., photos. (NACA RM L9I01) 

THE DAMPING IN ROLL OF ROCKET-POWERED 
TEST VEHICLES HAVING RECTANGULAR WINGS 
WITH NACA 65-006 AND SYMMETRICAL DOUBLE- 
WEDGE AIRFOIL SECTIONS OF ASPECT RATIO 4.5. 
Albert E. Dietz and James L. Edmondson. March 29, 
1950. 12p. diagrs. (NACA RM L50B10) 

DAMPING IN ROLL OF RECTANGULAR WINGS OF 
SEVERAL ASPECT RATIOS AND NACA 65A-SERIES 
AIRFOIL SECTIONS OF SEVERAL THICKNESS 
RATIOS AT TRANSONIC AND SUPERSONIC SPEEDS 
AS DETERMINED WITH ROCKET-POWERED 
MODELS. James L. Edmondson. August 24, 1950. 
16p. diagrs. (NACA RM L50E26) 



AERODYNAMICS 

WINGS (1.2) 23 



Variables - Complete Wings 
(Cont. ) 

TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED IN 
FLIGHT ON THE WING OF THE DOUGLAS D-558-I 
AIRPLANE FOR A 1 g STALL, A SPEED RUN TO A 
MACH NUMBER OF 0.90, AND A WIND-UP TURN 
AT A MACH NUMBER OF 0.86. Earl R. Keener and 
Mary Pierce. December 15, 1950. 40p. diagrs., 
photos., 5 tabs. (NACA RM L50J10) 

TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASI3RED 
IN FLIGHT ON THE WING OF THE DOUGLAS 
D-558-I AIRPLANE THROUGHOUT THE NORMAL- 
FORCE -COEFFICIENT RANGE AT MACH NUMBERS 
OF 0.67, 0.74, 0.78, AND 0.82. Earl R. Keener, 
James R. Peele and Julia B. Woodbridge. 
January 29, 1951. 37p. diagrs., photos., 6 tabs. 
(NACA HM L50L12a) 

THE EFFECT OF END PLATES, END STRUTS, 
AND DEPTH OF SUBMERGENCE ON THE CHAR- 
ACTERISTICS OF A HYDROFOIL. Kenneth L. 
Wadlin, Rudolph E. Fontana and Charles L. Shuford, 
Jr. April 12, 1951. 84p. diagrs., photos. (NACA 
RM L51B13) 

EFFECTS OF SPANWISE THICKNESS VARIATION 
ON THE AERODYNAMIC CHARACTERISTICS OF 
35° AND 45° SWEPTBACK WINGS OF ASPECT 
RATIO 6. TRANSONIC-BUMP METHOD. WilUam 
D. Morrison, Jr. and Paul G. Fournier. July 1951. 
38p. diagrs., photo. (NACA RM L51D19) 

TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED IN 
FLIGHT ON THE WING OF THE D-558-I RESEARCH 
AIRPLANE THROUGH A MACH NUMBER RANGE 
OF 0.80 TO 0.89 AND THROUGHOUT THE 
NORMAL-FORCE-COEFFICIENT RANGE AT MACH 
NUMBERS OF 0.61, 0.70, 0.855, AND 0.88. Earl 
R. Keener and Rozalia M. Bandlsh. August 1951. 
43p. diagrs., photos., 7 tabs. (NACA RM L51F12) 

A METHOD FOR THE DESIGN OF SWEPTBACK 
WINGS WARPED TO PRODUCE SPECIFIED FLIGHT 
CHARACTERISTICS AT SUPERSONIC SPEEDS. 
Warren A. Tucker. September 1951. 52p. diagrs., 

2 tabs. (NACA RM L51F08) 

EFFECTS OF SPANWISE THICKNESS VARIATION 
ON THE TRANSONIC AERODYNAMIC CHARACTER- 
ISTICS OF WINGS HAVING 35° OF SWEEPBACK, 
ASPECT RATIO 4, AND TAPER RATIO 0.60. 
William D. Morrison, Jr. and Paul G. Fournier. 
September 1951. 21p. diagrs., photo. (NACA 
RM L51F28) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A WING HAVING 45° SWEEP, ASPECT 
RATIO 8, TAPER RATIO 0.45, AND AIRFOIL 
SECTIONS VARYING FROM THE NACA 63A010 
SECTION AT THE ROOT TO THE NACA 63A006 
SECTION AT THE TIP. William D. Morrison, Jr. 
and Paul G. Fournier. January 1952. 22p. diagrs., 
photo. (NACA RM L51H28) 

SMALL-SCALE INVESTIGATION OF THE EFFECTS 
OF TWIST AND CAMBER ON THE AERODYNAMIC 
CHARACTERISTICS OF A 60° 42' SWEPTBACK 
WING OF ASPECT RATIO 1.94. Kenneth P. 
Spreemann and William J. Alford, Jr. January 1952. 
19p. diagrs., photo., tab. (NACA RM L51I21) 

A CORRELATION BY MEANS OF THE TRANSONIC 
SIMILARITY RULES OF THE EXPERIMENTALLY 
DETERMINED CHARACTERISTICS OF 22 RECTAN- 
GULAR WINGS OF SYMMETWCAL PROFILE. 
John B. McDevltt. February 1952. 60p. diagrs., 

3 tabs. (NACA RM A51L17b) 



LOW -SPEED STATIC LONGITUDINAL STABILITY 
AND CONTROL CHARACTERISTICS OF 60° 
TRIANGULAR -WING AND MODIFIED 60° 
TRIANGULAR-WING MODELS HAVING HALF- 
DELTA AND HALF-DIAMOND TIP CONTROLS. 
Jacob H. Lichtensteln and Byron M. Jaquet. 
February 1952. 36p. diagrs., photos., tab. (NACA 
RM L51K08) 

AN INVESTIGATION OF THE LOW -SPEED LONO- 
TUDINAL STABILITY CHARACTERISTICS OF A 
SWEPT -WING AIRPLANE MODEL WITH TWO MODI- 
FICATIONS TO THE WING-ROOT PLAN FORM. 
William B. Kemp, Jr. July 1952. 17p. diagrs., 
tab. (NACA RM L52E07) 

AN ANALYSIS OF ESTIMATED AND EXPERIMENT- 
AL TRANSONIC DOWNWASH CHARACTERISTICS 
AS AFFECTED BY PLAN FORM AND THICKNESS 
FOR WING AND WING-FUSELAGE CONFIGURA- 
TIONS. Joseph Weil, George S. CampbeU and 
Margaret S. Dlederich. November 1952. 92p. 
diagrs. , 2 tabs. (NACA RM L52I22) 

INVESTIGATION OF THREE TAPERED 45° SWEPT- 
BACK CAMBERED AND TWISTED WINGS COVER- 
ING A SIMULTANEOUS VARIATION IN ASPECT 
RATIO AND THICKNESS RATIO AND OF ONE RE- 
LATED SYMMETRICAL WING AT TRANSONIC 
SPEEDS BY THE WING-FLOW METHOD. Harold I. 
Johnson. March 1953. 55p. diagrs., photos., 2 tabs. 
(NACA RM L52H07) 

TABLES FOR THE COMPUTATION OF WAVE DRAG 
OF ARROW WINGS OF ARBITRARY AIRFOIL SEC- 
TION. Frederick C. Grant and Morton Cooper. 
June 1954. 9p. diagr., 28p. tabs, (in pocket) (NACA 
TN 3185) 

DESIGN CONSIDERATIONS FOR WINGS HAVING 
MINIMUM DRAG DUE TO LIFT. Warren A. Tucker. 
December 1954. 26p, diagrs. (NACA TN 3317) 

GENERAL THEORY OF CONICAL FLOWS AND ITS 
APPLICATION TO SUPERSONIC AERODYNAMICS. 
(La theorie generate des mouvements coniques et 
ses applications a I'aerodynamique supersonlque). 
Paul Germain. PREFACE. M. J. Peres. 
January 1955. vii, 333p. diagrs. (NACpA 
TM 1354. Trans, from Office National d'^tudes et 
de Recherches Aeronautiques, Pub. 34, 1949) 



Profiles 
(1.2.2.2.1) 

MEASUREMENTS OF THE EFFECTS OF THICK- 
NESS RATIO AND ASPECT RATIO ON THE DRAG 
OF RECTANGULAR-PLAN-FORM AIRFOILS AT 
TRANSONIC SPEEDS. Jim Rogers Thompson and 
Charles W. Mathews. June 20, 1947. 17p. diagrs., 
photo. (NACA RM L7E08) 

FUGHT TESTS TO DETERMINE THE EFFECT OF 
AIRFOIL SECTION PROFILE AND THICKNESS 
RATIO ON THE ZERO-LIFT DRAG OF LOW- 
ASPECT-RATIO WINGS AT SUPERSONIC SPEEDS. 
EUis Katz. February 9, 1948. 19p. diagrs., plwtos. 
(NACA RM L7K14) 

INVESTIGATION AT SUPERSONIC SPEED (M = 1. 53) 
OF THE PRESSURE DISTRIBUTION OVER A 63° 
SWEPT AIRFOIL OF BICONVEX SECTION AT 
ZERO LIFT. Charles W. Frick and John W. Boyd. 
June 10, 1948. 33p. diagrs. , photos. (NACA 
RM A8C22) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE. D-558-1 SPEED-REDUCTION BRAKE 
AND SYMMETRICAL-PROFILE WING CHARACTER- 
ISTICS. John B. Wright. June 15, 1948. 22p. 
diagrs., tab. (NACA RM L8B06) 



AERODYNAMICS 
24 WINGS (1.2) 



Profiles - Complete Wings (Cont. ) 

PRELIMINARY FREE-FUGHT INVESTIGATION 01' 
THE EFFECT OF AIRFOIL SECTION ON AILERON 
ROLLING EFFECTIVENESS AT TRANSONIC AND 
SUPERSONIC SPEEDS. Carl A. Sandahl. June 25, 
1948. 6p. dlagrs. (NACA RM L8B26) 

LANDING CHARACTERISTICS OF HIGH-SPEED 
WINGS. Herbert A. Wilson, Jr. and Laurence K. 
Loftin, Jr. September 21, 1948. 21p. diagrs. 
(NACA RM L8A28e) 

INVESTIGATION AT SUPHISONIC SPEED (M = 1.53) 
OF THE PRESSURE DISTRIBUTION OVER A 63° 
SWEPT AIRFOIL OF BICONVEX SECTION AT SEV- 
ERAL ANGLES OF ATTACK. John W. Boyd, EUiott 
D. Katzen and Charles W. Frick. September 24, 
1948. 41p. dlagrs., photos., tab. (NACA RM A8F22) 

EFFECT OF WING SWEEP, TAPER, AND THICK- 
NESS RATIO ON THE TRANSONIC DRAG CHARAC- 
TERISTICS OF WING-BODY COMBINATIONS. Jim 
Rogers Thompson and Charles W. Mathews. 
December 31, 1948. 29p. diagrs., photos., 2 tabs. 
(NACA RM L8K01) 

REDUCTION OF PROFILE DRAG AT SUPERSONIC 
VELOCITIES BY THE USE OF AIRFOIL SECTIONS 
HAVING A BLUNT TRAILING EDGE. Dean R. 
Chapman. November 1, 1949. 31p. diagrs., photo. 
(NACA RM A9H11) 

EFFECT OF AIRFOIL SECTION AND TIP TANKS 
ON THE AERODYNAMIC CHARACTERISTICS AT 
HIGH SUBSONIC SPEEDS OF AN UNSWEPT WING 
OF ASPECT RATIO 5. 18 AND TAPER RATIO 0.61. 
H. Norman Silvers and Kenneth P. Spreemann. 
December 1, 1949. 30p. diagrs., photos., 2 tabs. 
(NACA RM L9J04) 

FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.6 to 1.7 TO DETERMINE DRAG AND BASE 
PRESSURES ON A BLUNT -TRAILING-EDGE AIR- 
FOIL AND DRAG OF DIAMOND AND CIRCULAR- 
ARC AIRFOILS AT ZERO LIFT. John D. Morrow 
and Ellis Katz. August 11, 1950. 25p. diagrs., 
photos. (NACA RM L50E 19a) 

MEASUREMENTS OF THE EFFECT OF TRAILING- 
EDGE THICKNESS ON THE ZERO-LIFT DRAG OF 
THIN LOW-ASPECT-RATIO WINGS. John D. 
Morrow. August 14, 1950. 12p. diagrs., photo. 
(NACA RM L50F26) 

AERODYNAMIC CHARACTERISTICS AT A MACH 
NimBER OF 1.38 OF FOUR WINGS OF ASPECT 
RATIO 4 HAVING QUARTER-CHORD SWEEP 
ANGLES OF 0°, 35°, 45°, AND 60O. WUliam B. 
Kemp, Jr., Kenneth W. Goodson and Robert A. Booth. 
October 10, 1950. 41p. diagrs., photos., tab. 
(NACA RM L50G14) 

THE EFFECTS OF MACH NUMBER AND REYNOLDS 
NUMBER ON THE AERODYNAMIC CHARACTERIS- 
TICS OF SEVERAL 12-PERCENT -THICK WINGS 
HAVING 350 OF SWEEPBACK AND VARIOUS 
AMOUNTS OF CAMBER. Bruce E. Tinllng and W. 
Richard Kolk. February 23, 1951. 68p. dlagrs., 
photo., tab. (NACA RM A50K27) 

THE TRANSONIC CHARACTERISTICS OF 17 • 
RECTANGULAR, SYMMETRICAL WING MODELS 
OF VARYING ASPECT RATIO AND THICKNESS. 
Warren H. Nelson and John B. McDevitt. May 10, 
1951. 91p. diagrs., photos. (NACA RM A51A12) 

COMPARISON OF AIRFOIL SECTIONS ON TWO 
TRIANGULAR-WING- FUSELAGE CONFIGURATIONS 
AT TRANSONIC SPEEDS FROM TESTS BY THE 
NACA WING-FLOW METHOD. Albert W. Hall and 
James M. McKay. August 1951. 23p. diagrs., 
photo., tab. (NACARM L51F01) 



SUMMARY OF RESULTS OBTAINED BY 
TRANSONIC -BUMP METHOD ON EFFECTS OF 
PLAN FORM AND THICKNESS OF LIFT AND DRAG 
CHARACTERISTICS OF WINGS AT TRANSONIC 
SPEEDS. Edward C. Polhamus. November 1951. 
33p. diagrs., tab. (NACA RM L51H30) 

THE EFFECTS AT TRANSONIC SPEEDS OF THICK- 
ENING THE TRAILING EDGE OF A WING WITH A 
4-PERCENT -THICK CIRCULAR-ARC AIRFOIL. 
Joseph W. Cleary and George L. Stevens. December 
1951. 43p. dlagrs., photo. (NACA RM A51J11) 

THE TRANSONIC CHARACTERKTICS OF 38 CAM- 
BERED RECTANGULAR WINGS OF VARYING AS- 
PECT RATIO AND THICKNESS AS DETERMINED BY 
THE TRANSONIC-BUMP TECHNIQUE. Warren H. 
Nelson and Walter J. Krumm. July 1952. 173p. 
diagrs., photos. (NACA RM A52D11) 

EFFECT OF TRAILING-EDGE THICKNESS ON LIFT 
AT SUPERSONIC VELOCITIES. Dean R. Chapman 
and Robert H. Kester. July 1952. 24p. diagrs., 
photos. (NACA RM A52D17) 

EFFECTS OF PLAN FORM, AIRFOIL SECTION, 
AND ANGLE OF ATTACK ON THE PRESSURES 
ALONG THE BASE OF BLUNT -TRAILING-EDGE 
WINGS AT MACH NUMBERS OF 1.41, 1.62, AND 
1.96. Kennith L. Coin. September 1952. 52p. 
photos., diagrs. (NACA RM L52D21) 

FORCE TESTS OF THREE THIN WINGS OF MOD- 
ERATELY LOW ASPECT RATIO AT HIGH SUB- 
SONIC MACH NUMBERS. Gareth H. Jordan. 
October 1952. 22p. diagrs. (NACA RM L52I08) 

AERODYNAMIC CHARACTERBTICS OF TWO 
DELTA WmCB AT MACH NUMBER 4.04 AND COR- 
RELATIONS OF LIFT AND MINIMUM -DRAG DATA 
FOR DELTA WINGS AT MACH NUMBERS FROM 1.62 
TO 6.9. Edward F. Ulmann and Robert W. Dunning. 
December 1952. 20p. diagrs. (NACA RM L52K19) 

INVESTIGATION OF THREE TAPERED 45° SWEPT- 
BACK CAMBERED AND TWISTED WINCK COVER- 
ING A SIMULTANEOUS VARIATION IN ASPECT 
RATIO AND THICKNESS RATIO AITO OF ONE RE- 
LATED SYMMETRICAL WING AT TRANSONIC 
SPEEDS BY THE WING-FLOW METHOD. Harold I. 
Johnson. March 1953. 55p. diagrs., photos., 2 tabs. 
(NACA RM L52H07) 

A CORRELATION BY MEANS OF TRANSONIC 
SIMILARITY RULES OF THE EXPERIMENTALLY 
DETERMINED CHARACTERISTICS OF 18 CAM- 
BERED WINGS OF RECTANGULAR PLAN FORM. 
John B. McDevitt. September 1953. 57p. diagrs. 
(NACARM A53G31) 

TABLES FOR THE COMPUTATION OF WAVE DRAG 
OF ARROW WINGS OF ARBITRARY AIRFOIL SEC- 
TION. Frederick C. Grant and Morton Cooper. 
June 1954. 9p. diagr., 28p. tabs, (in pocket) (NACA 
TN 3185) 



Aspect Ratio 
(1.2.2.2.2) 



MEASUREMENTS OF THE EFFECTS OF THICK- 
NESS RATIO AND ASPECT RATIO ON THE DRAG 
OF RECTANGULAB-PLAN-FORM AIRFOILS AT 
TRANSONIC SPEEDS. Jim Rogers Thompson and 
Charles W. Mathews. June 20, 1947. 17p. diagrs., 
photo. (NACA RM L7E08) 



AERODYNAMICS 
WINGS (1.2) 



25 



Aspect Ratio - Complete Wings 
(Cont. ) 

APPLICATION OF ONE PART OF VON RAHMAN'S 
TWO-DIMENSIONAL TRANSONIC SIMILARITY LAW 
TO DRAG DATA OF NACA 65 -SERIES WINGS. 
Kenneth B. Amer. August 24, 1948. 9p. diagrs. 
(NACA RM L8F24) 

LANDING CHARACTERISTICS OF HIGH-SPEED 
WINGS. Herbert A. Wilson, Jr. and Laurence K. 
Loftin, Jr. September 21, 1948. 21p. diagrs. 
(NACA RM L8A28e) 



LOW -SPEED INVESTIGATION OF DEFLECTABLE 
WING-TIP AILERONS ON AN UNTAPERED 45° 
SWEPTBACK SEMISPAN WING WITH AND WITHOUT 
AN END PLATE. Jack Fischel and James M. 
Watson. December 14, 1949. 32p. diagrs., photo. 
(NACA RM L9J28) 

THE EFFECT OF ASPECT RATIO ON THE SUB- 
SONIC AERODYNAMIC CHARACTERISTICS OF 
WINGS WITH NACA 65i-210 SECTIONS. Warren H. 
Nelson and Albert L. Erlckson. February 3, 1950. 
31p. diagrs., photos., tab. (NACA RM A9K18) 

AERODYNAMIC INVESTIGATION AT MACH NUM- 
BER 1.92 OF A RECTANGULAR WING AND TAIL 
AND BODY CONFIGURATION AND ITS COMPO- 
NENTS. Macon C. Ellis, Jr. and Carl E. Grlgsby. 
March 1, 1950. 96p. diagrs., photos., 4 tabs. 
(NACA RM L9L28a) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LONGITUDINAL STABILITY AND CON- 
TROL. William B. Kemp, Jr. Robert E. Becht and 
Albert G. Few, Jr. March 14, 1950. 51p. diagrs., 
photos. (NACA RM L9K08) 

AERODYNAMIC CHARACTERBTICS AT A MACH 
NUMBER OF 1.25 OF A 6-PERCENT-THICK TRIAN- 
GULAR WING AND 6- AND 9-PERCENT-THICK TRI- 
ANGULAR WINGS IN COMBINATION WITH A FUSE- 
LAGE. WING ASPECT RATIO 2.31, BICONVEX AIR- 
FOIL SECTIONS. Albert W. Hall and Garland J. 
Morris. May 5, 1950. 22p. diagrs., photo., 2 tabs. 
(NACA RM L50D05) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LATERAL AND DIRECTIONAL STABILITY 
AND CONTROL. William B. Kemp, Jr. and Robert 
E. Becht. June 20, 1950. 97p. diagrs., photos. 
(NACA RM L50C17a) 

STABILITY CHARACTERISTICS AT LOW SPEED OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL WITH 
VARIOUS MODIFICATIONS TO THE BASIC MODEL 
CONFIGURATIONS. Robert E. Becht and Albert G. 
Few, Jr. August 16, 1950. 47p. diagrs., photo. 
(NACA RM L50F23) 

DAMPING IN ROLL OF RECTANGULAR WINGS OF 
SEVERAL ASPECT RATIOS AND NACA 65A-SERIES 
AIRFOIL SECTIONS OF SEVERAL THICKNESS 
RATIOS AT TRANSONIC AND SUPERSONIC SPEEDS 
AS DETERMINED WITH ROCKET-POWERED 
MODELS. James L. Edmondson. August 24, 1950. 
16p. diagrs. (NACA RM L50E26) 

FLIGHT TESTS AT SUPERSONIC SPEEDS TO 
DETERMINE THE EFFECT OF TAPER ON THE 
ZERO-UFT DRAG OF .SWEPTBACK LOW-ASPECT- 
RATIO WINGS. Murray Pittel. September 5, 1950. 
23p. diagrs., photos. (NACA RM L50F30a) 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AT HIGH-SUBSONIC SPEEDS OF TWO 
MODELS OF A TRANSONIC RESEARCH AIRPLANE 
WITH WINGS AND HORIZONTAL TAILS OF ASPECT 
RATIOS 4.2 AND 2. Arvo A. Luoma and John B. 
Wright. September 29, 1950. 134p. diagrs., photos., 
3 tabs. (NACA RM L50H07) 

PRELIMINARY EMPIRICAL DESIGN REQUIRE- 
MENTS FOR THE PREVENTION OF TUMBLING OF 
AIRPLANES HAVING NO HORIZONTAL TAILS. 
Robert L. Bryant. October 11, 1950. 23p. diagrs., 
2 tabs. (NACA RM L50H23) 

STABILITY AND CONTROL CHARACTERISTICS OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL IN 
THE LANDING CONFIGURATION. Robert E. Becht. 
December 18, 1950. 38p. diagrs., photos. (NACA 
RM L50J27) 

EFFECT OF AN END PLATE ON THE AERODY- 
NAMIC CHARACTERISTICS OF A 20.55° SWEPT- 
BACK WING WITH AN ASPECT RATIO OF 2.67 AND 
A TAPER RATIO OF 0.5. TRANSONIC -BUMP 
METHOD. James M. Watson. December 21, 1950. 
15p. diagrs., photo. (NACA RM L50H28a) 

THE EFFECT OF END PLATES, END STRUTS, 
AND DEPTH OF SUBMERGENCE ON THE CHAR- 
ACTERISTICS OF A HYDROFOIL. Kenneth L. 
Wadlin, Rudolph E. Fontana and Charles L. Shuford, 
Jr. April 12, 1951. 84p. diagrs., photos. (NACA 
RM L51B13) 

THE TRANSONIC CHARACTERISTICS OF 17 
RECTANGULAR, SYMMETRICAL WING MODELS 
OF VARYING ASPECT RATIO AND THICKNESS. 
Warren H. Nelson and John B. McDevitt. May 10, 
1951. 91p. diagrs., photos. (NACA RM A51A12) 

AERODYNAMIC CHARACTERISTICS OF TAPERED 
WINGS HAVING ASPECT RATIOS OF 4, 6, AND 8, 
QUARTER-CHORD LINES SWEPT BACK 45°, AND 
NACA 631A012 AIRFOIL SECTIONS. TRANSONIC- 
BUMP METHOD. Edward C. Polhamus and 
Thomas J. King, Jr. June 13, 1951. 23p. diagrs., 
photos., 2 tabs. (NACA RM L51C26) 

COMPARISON OF AIRFOIL SECTIONS Ok TWO 
TRIANGULAR-WING-FUSELAGE CONFIGURATIONS 
AT TRANSONIC SPEEDS FROM TESTS BY THE 
NACA WING-FLOW METHOD. Albert W. Hall and 
James M. McKay. August 1951. 23p. diagrs., 
photo., tab. (NACARML51F01) 

INVESTIGATION OF WING-TIP AILERONS ON A 
51.3° SWEPTBACK WING AT TRANSONIC SPEEDS 
BY THE TRANSONIC-BUMP METHOD. WilUam C. 
Moseley, Jr. and James M. Watson. November 1951. 
60p. diagrs. (NACA RM L51H27) 

SUMMARY OF RESULTS OBTAINED BY 
TRANSONIC -BUMP METHOD ON EFFECTS OF 
PLAN FORM AND THICKNESS OF LIFT AND DRAG 
CHARACTERISTICS OF WINGS AT TRANSONIC 
SPEEDS. Edward C. Polhamus. November 1951. 
33p. diagrs., tab. (NACA RM L51H30) 

EFFECTS OF HORIZONTAL-TAIL POSITION, AREA, 
AND ASPECT RATIO ON LOW-SPEED STATIC 
LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A 60° TRIANGULAR-WING 
MODEL HAVING VARIOUS TRIANGULAR-ALL- 
MOVABLE HORIZONTAL TAILS. Byron M. Jaquet. 
December 1951. 61p. diagrs., photo., tab. (NACA 
RM L51I06) 

PRESSURE DISTRIBUTION AT LOW SPEED ON A 
1/4-SCALE BELL X-5 AIRPLANE MODEL. 
William B. Kemp, Jr. and Albert G. Few, Jr. 
December 1951. 86p. diagrs., photos. (NACA 
RM L51I25) 



26 



AERODYNAMICS 
WINGS (1.2) 



Aspect Ratio - Complete Wings 
(Cont. ) 

INVESTIGATION OF THE LOW-SPEED AERODY- 
NAMIC CHARACTERISTICS OF A VARIABLE- 
SWEEP AIRPLANE MODEL WITH A TWISTED AND 
CAMBERED WING. William B. Kemp, Jr., Robert 
E. Becht and Albert G. Few, Jr. February 1952. 
62p. diagrs., photos. (NACA RM L51K22) 

THE TRANSONIC CHARACTERISTICS OF 38 CAM- 
BERED RECTANGULAR WINGS OF VARYING AS- 
PECT RATIO AND THICKNESS AS DETERMINED BY 
THE TRANSONIC-BUMP TECHNIQUE. Warren H. 
Nelson and Walter J. Krumm. July 1952. 173p. 
diagrs., photos. (NACA RM A52D11) 

EFFECT OF TRAILING-EDGE THICKNESS ON LIFT 
AT SUPERSONIC VELOCITIES. Dean R. Chapman 
and Robert H. Kester. July 1952. 24p. diagrs., 
photos. (NACA RM A52D17) 

PRELIMINARY STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTERIS- 
TICS OF THIN WINGS. A. Gerald Rainey. July 1952. 
33p. diagrs., photo., tab. (NACA RM L52D08) 

EFFECTS OF PLAN FORM, AIRFOIL SECTION. 
AND ANGLE OF ATTACK ON THE PRESSURES 
ALONG THE BASE OF BLUNT-TRAILING-EDGE 
WINGS AT MACH NUMBERS OF 1.41, 1.62, AND 
1.96. Kennith L. Goin. September 1952. 52p. 
photos., diagrs. (NACA RM L52D21) 

AN ANALYSIS OF ESTIMATED AND EXPERIMENT- 
AL TRANSONIC DOWNWASH CHARACTERISTICS 
AS AFFECTED BY PLAN FORM AND THICKNESS 
FOR WING AND WING-FUSELAGE CONFIGURA- 
TIONS. Joseph Weil, George S. Campbell and 
Margaret S. Dlederich. November 1952. 92p. 
diagrs. , 2 tabs. (NACA RM L52I22) 

INVESTIGATION OF THREE TAPERED 45° SWEPT- 
BACK CAMBERED AND TWBTED WINGS COVER- 
ING A SIMULTANEOUS VARIATION IN ASPECT 
RATIO AND THICKNESS RATIO AND OF ONE RE- 
LATED SYMMETRICAL WING AT TRANSONIC 
SPEEDS BY THE WING-FLOW METHOD. Harold I. 
Johnson. March 1953. 55p. diagrs., photos., 2 taba 
(NACA RM L52H07) 



A CORRELATION BY MEANS OF TRANSONIC 
SIMILARITY RULES OF THE EXPERIMENTALLY 
DETERMINED CHARACTERKTICS OF 18 CAM- 
BERED WINGS OF RECTANGULAR PLAN FORM. 
John B. McDevitt. September 1953. 57p. diagrs. 
(NACA RM A53G31) 

LIFT AND PITCHING MOMENT AT SUPERSONIC 
SPEEDS DUE TO CONSTANT VERTICAL ACCELER- 
ATION FOR THIN SWEPTBACK TAPERED WINGS 
WITH STREAMWISE TIPS. SUPERSONIC LEADING 
AND TRAILING EDGES. Isabella J. Cole and 
Kenneth Margolis. July 1954. 67p. diagrs., 4 tabs. 
(NACA TN 3196) 

THE HYDRODYNAMIC CHARACTERISTICS OF AN 
ASPECT -RATIO-0. 125 MODIFIED RECTANGULAR 
FLAT PLATE OPERATING NEAR A FREE WATER 
SURFACE. John A. Ramsen and Victor L. Vaughan, 
Jr. October 1954. 32p. diagrs. (NACA TN 3249) 



COMPARISON OF FLUTTER CALCULATIONS USING 
VARIOUS AERODYNAMIC COEFFICIENTS WITH 
EXPERIMENTAL RESULTS FOR SOME RECTANGU- 
LAR CANTILEVER WINGS AT MACH NUMBER 1.3. 
Herbert C. Nelson and Ruby A. Rainey. November 
1954. 22p. diagrs., 2 tabs. (NACA TN 33011 



A NOTE ON THE DRAG DUE TO LIFT OF REC- 
TANGULAR WINGS OF LOW ASPECT RATIO. 
Edward C. Polhamus. January 1955. 24p. diagrs. 
(NACA TN 3324) 

ON SLENDER DELTA WINGS WITH LEADING-EDGE 
SEPARATION. Clinton E. Brown and William H. 
Michael, Jr. April 1955. 27p. diagrs. (NACA 
TN 3430) 

ON THE KERNEL FUNCTION OF THE INTEGRAL 
EQUATION RELATING LIFT AND DOWNWASH DIS- 
TRIBUTIONS OF OSCILLATING WINGS IN SUPER- 
SONIC FLOW. Charles E. Watkins and Julian H. 
Berman. May 1955. 43p. (NACA TN 3438) 



Sweep 



(1.2.2.2.3) 

DRAG MEASUREMENTS OF A 34° SWEPT- 
FORWARD AND SWEPT -BACK NACA 65-009 AIR- 
FOIL OF ASPECT RATIO 2.7 AS DETERMINED BY 
FLIGHT TESTS AT SUPERSONIC SPEEDS. Sidney 
R. Alexander. February 20, 1947. lip. diagrs., 
photos. (NACA RM L6I11) 

DRAG OF A WING-BODY CONFIGURATION CON- 
SISTING OF A SWEPT-FORWARD TAPERED WING 
MOUNTED ON A BODY OF FINENESS RATIO 12 
MEASURED DURING FREE FALL AT TRANSONIC 
SPEEDS. Jim Rogers Thompson and Charles W. 
Mathews. March 13, 1947. 15p. diagrs., photos. 
(NACA RM L6L24) 

DRAG MEASUREMENTS OF A SWEPT -BACK WING 
HAVING INVERSE TAPER AS DETERMINED BY 
FLIGHT TESTS AT SUPERSONIC SPEEDS. Sidney 
R. Alexander. April 8, 1947. 12p. diagrs., photo. 
(NACA RM L6L30) 

OBSERVATIONS ON AN AILERON-FLUTTER IN- 
STABILITY ENCOUNTERED ON A 45° SWEPT- 
BACK WING IN TRANSONIC AND SUPERSONIC 
FLIGHT. Marvin Pitkin, William N. Gardner and 
Howard J. Curfman, Jr. April 11, 1947. 23p. 
diagrs., photos. (NACA RM L6L09) 

FLIGHT TESTS TO DETERMINE THE EFFECT OF 
TAPER ON THE ZERO-LIFT DRAG OF WINGS AT 
LOW SUPERSONIC SPEEDS. Sidney R. Alexander 
and Robert L. Nelson. July 13, 1947. 19p. diagrs., 
photos. (NACA RM L7E26) 

LONGITUDINAL STABIUTY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
WITH A SWEPTBACK WING AND TAIL FROM 
TESTS AT TRANSONIC SPEEDS BY THE NACA 
WING-FLOW METHOD. Richard H. Sawyer and 
Lindsay J. Lina. July 23, 1948. 42p. diagrs., 
photos., tab. (NACA RM L8B19) 

LANDING CHARACTERISTICS OF HIGH-SPEED 
WINGS. Herbert A. Wilson, Jr. and Laurence K. 
Loftin, Jr. September 21, 1948. 21p. diagrs. 
(NACA RM LBA28e) 

AN INVESTIGATION OF THE LOW-SPEED STATIC 
STABILITY CHARACTERISTICS OF COMPLETE 
MODELS HAVING SWEPTBACK AND SWEPT FOR- 
WARD WINGS. M. Leroy Spearman and Paul 
Comisarow. November 19, 1948. 51p. diagrs., tab. 
photos. (NACARM L8H31) 

EFFECT OF WING SWEEP, TAPER, AND THICK- 
NESS RATIO ON THE TRANSONIC DRAG CHARAC- 
TERISTICS OF WING-BODY COMBINATIONS. Tim 
Rogers Thompson and Charles W. Mathews. 
December 31, 1948. 29p. diagrs., photos., 2 tabs. 
(NACA RM L8K01) 



AERODYNAMICS 
WINGS (1,2) 



27 



Sweep - Complete Wings (Cont. ) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRAI©ONIC -BUMP 
METHOD. Joseph WeU and Kenneth W, Goodson. 
February 24, 1949. 28p. diagrs., photo., tab. 
(NACA RM L9A21) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER -CHORD LINE SWEPT BACK 35°, 
ASPECT RATIO 4, TAPER RATIO 0. 6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. William C. Sleeman, Jr. and Robert E. 
Becht. April 21, 1949. 29p. diagrs., photo., tab. 
(NACA RM L9B25) 

HIGH-SUBSONIC DAMPING-IN-ROLL CHARACTER<i 
ISTICS OF A WING WITH THE QUARTEB-CHORD 
LINE SWEPT BACK 35° AND WITH ASPECT RATK) 
3 AND TAPER RATIO 0.6. Boyd C. Myers, U and 
Richard E. Kuhn. May 10, 1949. 21p. diagrs., 
photo., tab. (NACA RM L9C23) 

EFFECTS OF MACH NUMBER AND SWEEP ON THE 
DAMPING-IN-ROLL CHARACTERISTICS OF WINGS 
OF ASPECT RATIO 4. Richard E. Kuhn and Boyd 

C. Myers, II. June 27, 1949. 28p. diagrs., photo. 
(NACA RM L9E10) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 4, TAPER RATIO 0.3, AND NACA 
eSAOOe AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Boyd C. Myers, II and Thomas J. King, 
Jr. July 20, 1949. 28p. diagrs., photo., tab. 
(NACA RM L9E25) 

DAMPING-IN-ROLL CHARACTERISTICS OF A 
42. 7° SWEPT-BACK WING AS DETERMINED FROM 
A WIND-TUNNEL INVESTIGATION OF A TWISTED 
SEMISPAN WING. Vernard E. Lockwood. August 8, 
1949. 23p. diagrs. (NACA RM L9F15) 

EFFECT OF SWEEPBACK ON THE LOW -SPEED 
STATIC AND ROLUNG STABILITY DERIVATIVES 
OF THIN TAPERED WINGS OF ASPECT RATIO 4. 
William Letko and Walter D. Wolhart. August 9, 
1949. 36p. diagrs., photo. (NACA RM L9F14) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER - 
CHORD LINE SWEPT BACK 45°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. Raymond 

D. Vogler. August 15, 1949. 22p. diagrs. (NACA 
RM L9F29a) 

AERODYNAMIC CHARACTERISTICS OF A DELTA 
WING WITH LEADING EDGE SWEPT BACK 45°, 
ASPECT RATIO 4, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. William 
C. Sleeman, Jr. and Robert E. Becht. September 6, 
1949. 29p. diagrs., photo., tab. (NACA 
RM L9G22a) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER -CHORD LINE SWEPT BACK 60°, 
ASPECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC-BUMP 
METHOD. Thomas J. King, Jr. and Boyd C. Myers, 
II. September 6, 1949. 32p. diagrs., photos., tab. 
(NACA RM L9G27) 

INVESTIGATION OF EXTENSIBLE WING-TIP 
AILERONS ON AN UNTAPERED SEMISPAN WING 
AT 0° AND 45° SWEEPBACK. John R. Hagerman 
and WlUiam M. O'Hare. September 20, 1949. 4Qp. 
diagrs., photo., tab. (NACA RM L9H04) 



AERODYNAMIC CHARACTERISTICS OF A WING 
WITH UNSWEPT QUARTER -CHORD LINE, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A006 
AIRFOIL SECTION. TRANSONIC -BUMP METHOD. 
Kenneth W. Goodson and William D. Morrison, Jr. 
October 21, 1949. 32p. diagrs., photos., tab. 
(NACA RM L9H22) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Kenneth W. Goodson and Albert G. Few, 
Jr. November 1, 1949. 34p. diagrs., photos., tab. 
(NACA RM L9I08) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER -CHORD LINE SWEPT BACK 35°, 
ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC-BUMP 
METHOD. William C. Sleeman, Jr. and William D. 
Morrison, Jr. December 12, 1949. 32p. diagrs., 
photos., tab. (NACA RM L9K10a) 

LATERAL -CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER- 
CHORD LINE SWEPT BACK 35°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC-BUMP METHOD. Robert F. 
Thompson. January 25, 1950. 22p. diagrs., tab. 
(NACA RM L9L12a) 

MAXIMUM -LIFT INVESTIGATION AT MACH NUM- 
BERS FROM 0.05 TO 1.20 OF A WING WITH LEAD- 
ING EDGE SWEPT BACK 42°. Thomas R. Turner. 
February 14, 1950. 21p. diagrs. (NACA 
RM L9K03) 

EXPLORATORY INVESTIGATION OF LEADING- 
EDGE CHORD-EXTENSIONS TO IMPROVE THE 
LONGITUDINAL STABILITY CHARACTERISTICS OF 
TWO 52° SWEPTBACK WINGS. G. Chester Furlong. 
March 10, 1950. 32p. diagrs., photo. (NACA 
RM L50A30) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LONGITUDINAL STABILITY AND CON- 
TROL. William B. Kemp, Jr. Robert E. Becht and 
Albert G. Few, Jr. March 14, 1950. 51p. diagrs., 
photos. (NACA RM L9K08) 

AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBER OF 1.25 OF A 6 -PERCENT-THICK TRIAN- 
GULAR WING AND 6- AND 9-PERCENT-THICK TRI- 
ANGULAR WINGS IN COMBINATION WITH A FUSE- 
LAGE. WING ASPECT RATIO 2.31, BICONVEX AIR- 
FOIL SECTIONS. Albert W. HaU and Garland J. 
Morris. May 5, 1950. 22p. diagrs., photo., 2 tabs. 
(NACA RM L50D05) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LATERAL AND DIRECTIONAL STABILITY 
AND CONTROL. William B. Kemp, Jr. and Robert 
E. Becht. June 20, 1950. 97p. diagrs., photos. 
(NACA RM L50C17a) 

INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
METHODS OF ALLEVIATING THE ADVERSE 
INTERFERENCE AT THE ROOT OF A SWEPT- 
BACK WING. Lee E. Boddy. August 10, 1950. 31p. 
diagrs., photos. (NACA RM A50E26) 

STABILITY CHARACTERISTICS AT LOW SPEED OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL WITH 
VARIOUS MODIFICATIONS TO THE BASIC MODEL 
CONFIGURATIONS. Robert E. Becht and Albert G. 
Few, Jr. August 16, 1950. 47p. diagrs., photo. 
(NACA RM L50F23) 



AERODYNAMICS 
28 WINGS (1.2) 



Sweep - Complete Wings {Cont. ) 

WING-FLOW MEASUREMENTS OF LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
A CANARD AIRPLANE CONFIGURATION WITH A 
450 SWEPTBACK WING AND A TRIANGULAR ALL- 
MOVABLE CONTROL SURFACE. Harold L. Crane 
and James J. Adams. August 25, 1950. 53p. 
diagrs., photo. (NACA RM L50A31) 

FLIGHT TESTS AT SUPERSONIC SPEEDS TO 
DETERMINE THE EFFECT OF TAPER ON THE 
ZERO-LIFT DRAG OF SWEPTBACK LOW-ASPECT- 
RATIO WINGS. Murray Pittel. September 5, 1950. 
23p. diagrs., photos. (NACA RM LSDFSOa) 

TRANSONIC DRAG CHARACTERISTICS OF A WING- 
BODY COMBINATION USING A THIN TAPERED 
WING OF 450 SWEEPBACK. Max C. Kurbjun and 
Stanley Faber. September 28, 1950. 14p. diagrs., 
photo., tab. (NACA RM L50H22) 

EFFECTS OF SWEEP ON THE MAXIMUM-LIFT 
CHARACTERISTICS OF FOUR ASPECT-RATIO-4 
WINGS AT TRANSONIC SPEEDS. Thomas R. Turner. 
October 3, 1950. 25p. diagrs. (NACA RM L50H11) 

AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBER OF 1.38 OF FOUR WiNGS OF ASPECT 
RATIO 4 HAVING QUARTER-CHORD SWEEP 
ANGLES OF 0°, 35°, 45°, AND 60°. WUllam B. 
Kemp, Jr., Kenneth W. Goodson and Robert A. Booth. 
October 10, 1950. 41p. diagrs., photos., tab. 
(NACA RM L50G14) 

LOW -SPEED INVESTIGATION OF THE EFFECT OF 
SEVERAL FLAP AND SPOILER AILERONS ON THE 
LATERAL CHARACTERISTICS OF A 47.5° 
SWEPTBACK-WING - FUSELAGE COMBINATION 
AT A REYNOLDS NUMBER OF 4.4 x lO^. Jerome 
Pasamanlck and Thomas B. Sellers. December 8, 
1950. 57p. diagrs., photo. (NACA RM L50J20) 

EFFECTS OF SWEEP ON THE DAMPING-IN-ROLL 
CHARACTERISTICS OF THREE SWEPTBACK 
WINGS HAVING AN ASPECT RATIO OF 4 AT 
TRANSONIC SPEEDS. Vernard E. Lockwood. 
December 14, 1950. 23p. diagrs. (NACA 
RM L50J19) 

STABmiTY AND CONTROL CHARACTERISTICS OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL IN 
THE LANDING CONFIGURATION. Robert E. Becht. 
December 18, 1950. 38p. diagrs., photos. (NACA 
RM L50J27) 

LONGITUDINAL-CONTROL EFFECTIVENESS AND 
DOWNWASH CHARACTERISTICS AT A MACH NUM- 
BER OF 1.24 OF A 1/30-SCALE SEMISPAN MODEL 
OF THE BELL X-5 AIRPLANE AS DETERMINED BY 
THE NACA WING-FLOW METHOD. Richard H. 
Sawyer, Robert M. Kennedy and Garland J. Morris. 
January 8, 1951. 37p. diagrs., photos., tab. 
(NACA RM L50K15) 

THE EFFECTS OF MACH NUMBER AND REYNOLDS 
NUMBER ON THE AERODYNAMIC CHARACTERIS- 
TICS OF SEVERAL 12-PERCENT-THICK WINGS 
HAVING 350 OF SWEEPBACK AND VARIOUS 
AMOUNTS OF CAMBER. Bruce E. Tlnling and W. 
Richard Kolk. February 23, 1951. 68p. diagrs., 
photo., tab. (NACA RM A50K27) 

EFFECT OF A DEFLECTABLE WING-TIP CON- 
TROL ON THE LOW -SPEED LATERAL AND 
LONGITUDINAL CHARACTERISTICS OF A LARGE- 
SCALE WING WITH THE LEADING EDGE SWEPT 
BACK 47.50. Roy H. Lange and Marvin P. Fink. 
April 26, 1951. 41p. diagrs., photo., 2 tabs. 
(NACA RM L51C07) 

PRESSURE -DISTRIBUTION MEASUREMENTS OVER 
A 45° SWEPTBACK WING AT TRANSONIC SPEEDS 
BY THE NACA WING-FLOW METHOD. Edward 
C. B. Danforth and Thomas C. O'Bryan. June 1951. 
42p. diagrs., photos. (NACA RM L51D24) 



AERODYNAMIC CHARACTERISTICS OF TAPERED 
WINGS HAVING ASPECT RATIOS OF 4, 6, AND 8, 
QUARTER-CHORD LINES SWEPT BACK 45°, AND 
NACA 631A012 AIRFOIL SECTIONS. TRANSONIC- 
BUMP METHOD. Edward C. Polhamus and 
Thomas J. King, Jr. June 13, 1951. 23p. diagrs., 
photos., 2 tabs. (NACA RM L51C26) 

AN EXPERIMENTAL STUDY AT MODERATE AND 
HIGH SUBSONIC SPEEDS OF THE FLOW OVER 
WINGS WITH 30° AND 45° OF SWEEPBACK IN 
CONJUNCTION WITH A FUSELAGE. Richard T. 
Whitcomb. June 15, 1951. 56p. diagrs., photos. 
(NACA RM L50K27) 

AN EXPERIMENTAL STUDY OF MODERATE AND 
HIGH SUBSONIC SPEEDS OF THE FLOW OVER 
WINGS WITH 30° AND 45° OF SWEEPFORWARD 
IN CONJUNCTION WITH A FUSELAGE. Richard T. 
Whitcomb. June 15, 1951. 47p. diagrs., photo. 
(NACA RM L50K28) 

EFFECTS OF SPANWISE THICKNESS VARIATION 
ON THE AERODYNAMIC CHARACTERISTICS OF 
35° AND 45° SWEPTBACK WINGS OF ASPECT 
RATIO 6. TRANSONIC -BUMP METHOD. William 
D. Morrison, Jr. and Paul G. Fournier. July 1951. 
38p. diagrs., photo. (NACA RM L51D19) 

COMPARISON OF AIRFOIL SECTIONS ON TWO 
TRIANGULAR-WING- FUSELAGE CONFIGURATIONS 
AT TRANSONIC SPEEDS FROM TESTS BY THE 
NACA WING-FLOW METHOD. Albert W. Hall and 
James M. McKay. August 1951. 23p. diagrs., 
photo., tab. (NACA RM L51F01) 

AERODYNAMIC CHARACTERISTICS AT TRAN- 
SONIC SPEEDS OF A TAPERED 45° SWEPTBACK 
WING OF ASPECT RATIO 3 HAVING A FULL-SPAN 
FLAP-TYPE CONTROL. TRANSONIC-BUMP 
METHOD. Vernard E. Lockwood and Joseph E. 
Fikes. August 1951. 35p. diagrs. (NACA 
RM L51F06a) 

SMALL-SCALE INVESTIGATION AT TRANSONIC 
SPEEDS OF THE EFFECTS OF THICKENING THE 
INBOARD SECTION OF A 45° SWEPTBACK WING 
OF ASPECT RATIO 4, TAPER RATIO 0.3, AND 
NACA 65A006 AIRFOIL SECTION. Kenneth P. 
Spreemann and WilUam J. Alford, Jr. August 1951. 
21p. diagrs., photo. (NACA RM L^lFOSa) 

EXPERIMENTAL STUDY OF THE EFFECT OF 
SWEEPBACK ON TRANSONIC AILERON FLUTTER. 
Lionel L. Levy, Jr. and Earl D. Knechtel. 
September 1951. 20p. diagra, photo. (NACA RM 
A51E04) 

LONGITUDINAL FREQUENCY-RESPONSE CHARAC- 
TERISTICS OF A 35° SWEPT-WDJG AIRPLANE AS 
DETERMINED FROM FLIGHT MEASUREMENTS, 
INCLUDING A METHOD FOR THE EVALUATION OF 
TRANSFER FUNCTIONS. William C. Triplett and G. 
Allan Smith. September 1951. 45p. diagrs., photo. 
(NACA RM A51G27) 

EFFECTS OF SPANWISE THICKNESS VARIATION 
ON THE TRANSONIC AERODYNAMIC CHARACTER- 
ISTICS OF WINGS HAVING 35° OF SWEEPBACK, 
ASPECT RATIO 4, AND TAPER RATIO 0.60. 
William D. Morrison, Jr. and Paul G. Fournier. 
September 1951. 21p. diagrs., photo. (NACA 
RM L51F28) 

THE EFFECTS ON THE AERODYNAMIC CHARAC- 
TERISTICS OF REVERSING THE WING OF A TRI- 
ANGULAR WING-BODY COMBINATION AT TRAN- 
SONIC SPEEDS AS DETERMINED BY THE NACA 
WING-FLOW METHOD. James M. McKay and 
Albert W. Hall. October 1951. 22p. diagrs., photo., 
2 tabs. (NACA RM L51H23) 

LOAD DISTRIBUTION OVER A FUSELAGE IN COM- 
BINATION WITH A SWEPT WING AT SMALL 
ANGLES OF ATTACK AND TRANSONIC SPEEDS. 
.Maurice D. White and Bonne C. Look. November 
1951. 26p. diagrs., photo., tab. (NACA RM 
A51H15) 



AERODYNAMICS 
WINGS (1,2) 



29 



Sweep - Complete Wings (Cont. ) 

A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH -UP OF A SWEPT -WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
Seth B. Anderson and Richard S. Bray. November 
1951. 33p. diagrs., photo., tab. (NACA RM A51I12) 

INVESTIGATION OF WING-TIP AILERONS ON A 
51.3° SWEPTBACK WING AT TRANSONIC SPEEDS 
BY THE TRANSONIC -BUMP METHOD. William C. 
Moseley, Jr. and James M. Watson. November 1951. 
60p. diagrs. (NACA RM L51H27) 

SUMMARY OF RESULTS OBTAINED BY 
TRANSONIC -BUMP METHOD ON EFFECTS OF 
PLAN FORM AND THICKNESS OF LIFT AND DRAG 
CHARACTERISTICS OF WINGS AT TRANSONIC 
SPEEDS. Edward C. Polhamus. November 1951. 
33p. diagrs., tab. (NACA RM L51H30) 

AERODYNAMIC CHARACTERISTICS OF A 
LEADING-EDGE SLAT ON A 35° SWEPT -BACK 
WING FOR MACH NITMBERS FROM 0.30 TO 0.88. 
John A. Kelly and Nora-Lee F. Hayter. December 
1951. 49p. diagrs., tab. (NACA RM A51H23) 

EFFECTS OF HORIZONTAL-TAIL POSITION, AREA, 
AND ASPECT RATIO ON LOW -SPEED STATIC 
LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A 60° TRIANGULAR-WING 
MODEL HAVING VARIOUS TRIANGULAR-ALL - 
MOVABLE HORIZONTAL TAILS. Byron M. Jaquet. 
December 1951. 61p. diagrs., photo., tab. (NACA 
RM L51I06) 

PRESSURE DISTRIBUTION AT LOW SPEED ON A 
1/4-SCALE BELL X-5 AIRPLANE MODEL. 
William B. Kemp, Jr. and Albert G. Few, Jr. 
December 1951. 86p. diagrs., photos. (NACA 
RM L51I25) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A WING HAVING 45° SWEEP, ASPECT 
RATIO 8, TAPER RATIO 0.45, AND AIRFOIL 
SECTIONS VARYING FROM THE NACA 63A010 
SECTION AT THE ROOT TO THE NACA 63A006 
SECTION AT THE TIP. William D. Morrison, Jr. 
and Paul G. Fournier. January 1952. 22p. diagrs., 
photo. (NACA RM L51H28) 

SMALL-SCALE INVESTIGATION OF THE EFFECTS 
OF TWIST AND CAMBER ON THE AERODYNAMIC 
CHARACTERISTICS OF A 60° 42' SWEPTBACK 
WING OF ASPECT RATIO 1.94. Kenneth P. 
Spreemann and William J. Alford, Jr. January 1952. 
19p. diagrs., photo., tab. (NACA RM L51I21) 

INVESTIGATION OF THE DISTRIBUTION OF LIFT, 
DRAG, AND PITCHING MOMENT BETWEEN THE 
WING AND FUSELAGE OF A 1/30-SCALE SEMI- 
SPAN MODEL OF THE BELL X-5 AIRPLANE AT A 
MACH NUMBER OF 1. 24 BY THE NACA WING- 
FLOW METHOD. Norman S. Silsby and Garland J. 
Morris. January 1952. 32p. diagrs. , photos. , 
tab. (NACA RM L51K27) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A TAPERED 45° SWEPTBACK WDJG 
OF ASPECT RATIO 3 HAVING A FULL-SPAN FLAP 
TYPE OF CONTROL WITH OVERHANG BALANCE. 
TRANSONIC -BUMP METHOD. Vernard E. 
Lockwood and John R. Hagerman. January 1952. 
24p. diagrs. (NACA RM L51L11) 

EFFECT OF CURRENT DESIGN TRENDS ON AIR- 
PLANE SPINS AND RECOVERIES. Anshal I. 
Neihouse. January 1952. 6p. diagrs. (NACA RM 
L52A09) 



THE EFFECTIVENESS OF WING VORTEX GENER- 
ATORS IN IMPROVING THE MANEUVERING CHAR- 
ACTERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, George 
A. Rathert, Jr. and Richard S. Bray. February 1952. 
45p. Dhotos., diagrs., tab. (NACA RM A51J18) 

LOW-SPEED WIND-TUNNEL INVESTIGATION OF A 
FIXED AND A FREE-FLOATING WDJG-TIP AILER- 
ON ON A WING WITH LEADING EDGE SWEPT 
BACK 51.3°. R. G. MacLeod. February 1952. 
17p. diagrs., photo., tab. (NACA RM L51H16a) 

LOW -SPEED STATIC LONGITUDINAL STABILITY 
AND CONTROL CHARACTERISTICS OF 60° 
TRIANGULAR -WING AND MODIFIED 60° 
TRIANGULAR-WING MODELS HAVING HALF- 
DELTA AND HALF-DIAMOND TIP CONTROLS. 
Jacob H. Lichtenstein and Byron M. Jaquet. 
February 1952. 36p. diagrs., photos., tab. (NACA 
RM L51K08) 

INVESTIGATION OF THE LOW-SPEED AERODY- 
NAMIC CHARACTERISTICS OF A VARIABLE- 
SWEEP AIRPLANE MODEL WITH A TWISTED AND 
CAMBERED WING. William B. Kemp, Jr., Robert 
E. Becht and Albert G. Few, Jr. February 1952. 
62p. diagrs., photos. (NACA RM L51K22) 

THE INTERFERENCE EFFECTS OF A BODY ON 
THE SPANWISE LOAD DISTRIBUTIONS OF TWO 
45° SWEPTBACK WINGS OF ASPECT RATIO 8 
FROM LOW -SPEED TESTS AT A REYNOLDS 
NUMBER OF 4 X 10^. Albert P. Martina. February 
1952. 48p. diagrs., photo., 2 tabs. (NACA 
RM L51K23) 

FLUTTER INVESTIGATION OF TWO THIN, LOW- 
ASPECT-RATIO, SWEPT, SOLID, METAL WINGS 
IN THE TRANSONIC RANGE BY USE OF A FREE- 
FALLING BODY. W. T. Lauten, Jr. and Maurice 
A. Sylvester. February 1952. 12p. diagrs., photo., 
2 tabs. (NACA RM L51K28a) 

WIND-TUNNEL INVESTIGATION AT HIGH AND LOW 
SUBSONIC MACH NUMBERS OF A THIN SWEPT- 
BACK WING HAVING AN AIRFOIL SECTION DE- 
SIGNED FOR HIGH MAXIMUM 'LIFT. Stanley F. 
Racisz and Nicholas J. Paradiso. February 1952. 
46p. diagrs., photo., tab. (NACA RM L51L04) 

HINGE -MOMENT AND OTHER AERODYNAMIC 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
QUARTER-SPAN SPOILER ON A TAPERED 45° 
SWEPTBACK WING OF ASPECT RATIO 3. 
Joseph E. Fikes. February 1952. 22p. diagrs., 
photo. (NACA RM L52A03) 

PRELIMINARY INVESTIGATION OF CONTROL 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3 HAVING A HORN-BALANCED FULL-SPAN 
CONTROL. John G. Lowry and Joseph E. Fikes. 
April 1952. 22p. diagrs., photo. (NACA RM 
L52A11) 

LOW-SPEED STABILITY CHARACTERISTICS OF A 
COMPLETE MODEL WITH A WING OF W PLAN 
FORM. Edward C. Polhamus and Robert E. Becht. 
April 1952. 27p. diagrs., photo., tab. (NACA 
RM L52A25) 

EFFECTS OF HORIZONTAL-TAIL POSITION AND 
ASPECT RATIO ON LOW -SPEED STATIC LONGI- 
TUDINAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF A 60° TRIANGULAR -WING MODEL HAV- 
ING TWIN TRIANGULAR ALL-MOVABLE TAILS. 
Byron M. Jaquet. May 1952. 45p. diagrs., photos. 
(NACA RM L52B25) 



AERODYNAMICS 
30 WINGS (1.2) 



Sweep - Complete Wings (Cont. ) 

SMALL-SCALE TRANSONIC INVESTIGATION OF 
THE EFFECTS OF PARTIAL-SPAN LEADING-EDGE 
CAMBER ON THE AERODYNAMIC CHARACTERIS- 
TICS OF A 50O 38' SWEPTBACK WING OF ASPECT 
RATIO 2.98. William J. Alford, Jr. and Andrew L. 
Byrnes, Jr. June 1952. 28p. diagrs., photo., tab. 
(NACA RM L52D08a) 

PRELMINARy STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTERIS- 
TICS OF THIN WINGS. A. Gerald Rainey. July 1952. 
33p. diagrs., photo., tab. (NACA RM L52D08) 

CONTROL CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A LINKED FLAP AND SPOILER ON A 
TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3. Vernard E. Lockwood and Joseph E. 
Fikes. July 1952. 24p. diagrs., photo. (NACA 
RM L52D25) 

AN INVESTIGATION OF THE LOW -SPEED LONGI- 
TUDINAL STABILITY CHARACTERISTICS OF A 
SWEPT -WING AIRPLANE MODEL WITH TWO MODI- 
FICATIONS TO THE WING-ROOT PLAN FORM. 
William B. Kemp, Jr. July 1952. 17p. diagrs., 
tab. (NACA RM L52E07) 

SMALL-SCALE TRANSONIC INVESTIGATION OF 
THE EFFECTS OF FULL-SPAN AND PARTIAL- 
SPAN LEADING-EDGE FLAPS ON THE AERO- 
DYNAMIC CHARACTERISTICS OF A 50° 38' SWEPT- 
BACK WING OF ASPECT RATIO 2.98. Kenneth P. 
Spreemann and William J. Alford, Jr. July 1952. 
31p. diagrs., photo. (NACA RM L52E12) 

CONTROL EFFECTIVENESS AND HINGE-MOMENT 
CHARACTERISTICS AT LOW SPEED OF LARGE- 
CHORD, HORN-BALANCED, FLAP-TYPE CON- 
TROLS ON A TRIANGULAR WING OF ASPECT 
RATIO 2. Jutes B. Dods, Jr. August 1952. 53p. 
diagrs., photos., 2 tabs. (NACA RM A52F13) 

LATERAL-CONTROL INVESTIGATION AT TRAN- 
SONIC SPEEDS OF RETRACTABLE SPOILER AND 
PLUG-TYPE SPOILER-SLOT AILERONS ON A 
TAPERED 60° SWEPTBACK WING OF ASPECT 
RATIO 2. TRANSONIC -BUMP METHOD. Alexander 
D. Hammond and James M. Watson. August 1952. 
19p. diagrs. (NACA RM L52F16) 

HINGE-MOMENT AND CONTROL-EFFECTIVENESS 
CHARACTERISTICS OF AN OUTBOARD FLAP WITH 
AN OVERHANG NOSE BALANCE ON A TAPERED 
35° SWEPTBACK WING OF ASPECT RATIO 4. 
TRANSONIC -BUMP METHOD. Robert F. Thompson 
and William C. Moseley, Jr. August 1952. 51p. 
diagrs. (NACA RM L52G08) 

EFFECTS OF PLAN FORM, AIRFOIL SECTION, 
AND ANGLE OF ATTACK ON THE PRESSURES 
ALONG THE BASE OF BLUNT -TRAILING-EDGE 
WINGS AT MACH NUMBERS OF 1.41, 1.62, AND 
1.96. Kennith L. Goin. September 1952. 52p. 
photos., diagrs. (NACA RM L52D21) 

THE EFFECT OF VARIOUS AERODYNAMIC BAL- 
ANCES ON THE LOW-SPEED LATERAL-CONTROL 
AND HINGE-MOMENT CHARACTERISTICS OF A 
0.20-CHORD PARTIAL-SPAN OUTBOARD AILERON 
ON A WING WITH LEADING EDGE SWEPT BACK 
51.3°. Alexander D. Hammond. September 1952. 
40 p. diagrs., photo., tab. (NACA RM L52G03) 

LOW-SPEED LATERAL-CONTROL INVESTIGATION 
OF A FLAP-TYPE SPOILER AILERON WITH AND 
WITHOUT A DEFLECTOR AND SLOT ON A 6- 
PERCENT -THICK, TAPERED, 45° SWEPTBACK 
WING OF ASPECT RATIO 4. James M. Watson. 
September 1952. lip. diagrs. (NACA RM L52G10) 



AN ANALYSIS OF ESTIMATED AND EXPERIMENT- 
AL TRANSONIC DOWNWASH CHARACTERISTICS 
AS AFFECTED BY PLAN FORM AND THICKNESS 
FOR WING AND WING-FUSELAGE CONFIGURA- 
TIONS. Joseph Weil, George S. Campbell and 
Margaret S. Diederich. November 1952. 92p. 
diagrs. , 2 tabs. (NACA RM L52I22) 

INVESTIGATION AT TRANSONIC SPEEDS OF THE 
EFFECT OF A POSITIVE-UFT BALANCING TAB 
ON THE HINGE -MOMENT AND UFT CHARACTER- 
ISTICS OF A FULL-SPAN FLAP ON A TAPERED 
45° SWEPTBACK WING OF ASPECT RATIO 3. 
Vernard E. Lockwood and Joseph E. Fikes. 
November 1952. 22p. diagrs. , photo. (NACA 
RM L52J09) 

A WIND-TUNNEL INVESTIGATION AT LOW 
SPEEDS OF THE AERODYNAMIC CHARACTER- 
ISTICS OF VARIOUS SPOILER CONFIGURATIONS 
ON A THIN 60° DELTA WING. Harleth G. Wiley 
and Martin Solomon. November 1952. 20p. diagrs. 
(NACA RM L52J13) 

FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW -SPEED STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A MODEL HAVING A FUSELAGE 
OR RELATIVELY FLAT CROSS SECTION. John W. 
Paulson and Joseph L. Johnson, Jr. February 1953. 
30p. diagrs., photo., tab. (NACA RM L52L22) 

INVESTIGATION OF THREE TAPERED 45° SWEPT- 
BACK CAMBERED AND TWISTED WINGS COVER- 
ING A SIMULTANEOUS VARIATION IN ASPECT 
RATIO AND THICKNESS RATIO AND OF ONE RE- 
LATED SYMMETRICAL WING AT TRANSONIC 
SPEEDS BY THE WING-FLOW METHOD. Harold I. 
Johnson. March 1953. 55p. diagrs., photos., 2 tabs. 
(NACA RM L52H07) 

A COMPARISON OF GUST LOADS MEASURED IN 
FLIGHT ON A SWEPT -WING AIRPLANE AND AN 
UNSWEPT-WING AIRPLANE. Jack Funk and 
Harry C. Mlckleboro. June 1953. 16p. diagrs., 
2 tabs. (NACA RM L52L02) 

SOME OBSERVATIONS ON STALL FLUTTER AND 
BUFFETING. A. Gerald Rainey. June 1953. lip. 
diagrs. (NACA RM L53E15) 

THE AERODYNAMIC CHARACTERISTICS AT 
TRANSONIC SPEEDS OF AN ALL-MOVABLE, 
TAPERED, 45° SWEPTBACK, ASPECT-RATIO-4 
TAIL DEFLECTED ABOUT A SKEWED HINGE AXIS 
AND EQUIPPED WITH AN INSET UNBALANCING 
TAB. James M. Watson. September 1953. 40p. 
diagrs. (NACA RM L53H13) 

THE CALCULATION OF PRESSURE ON SLENDER 
AIRPLANES IN SUBSONIC AND SUPERSONIC FLOW. 
Max. A. Heaslet and Harvard Lomax. 1954. ii. 
lip. diagrs. (NACA Rept. 1185. Formerly TN 2900) 

LIFT AND PITCHING MOMENT AT SUPERSONIC 
SPEEDS DUE TO CONSTANT VERTICAL ACCELER- 
ATION FOR THIN SWEPTBACK TAPERED WINGS 
WITH STREAMWISE TIPS. SUPERSONIC LEADING 
AND TRAILING EDGES. Isabella J. Cole and 
Kenneth MargoUs. July 1954. 67p. diagrs., 4 tabs. 
(NACA TN 3196) 

LOW-SPEED WIND-TUNNEL INVESTIGATION OF A 
TRIANGULAR SWEPTBACK AIR INLET IN THE 
ROOT OF A 45° SWEPTBACK WING. Arvid L. 
Keith, Jr. and Jack Schiff. January 1955. 65p. 
diagrs., photos., 5 tabs. (NACA TN 3363. Formerly 
RM L50I01) 

TOTAL LIFT AND PITCHING MOMENT ON THIN 
ARROWHEAD WINGS OSCILLATING IN SUPERSONIC 
POTENTIAL FLOW. H. J. Cunningham. May 1955. 
43p. diagrs., 4 tabs. (NACA TN 3433) 



AERODYNAMICS 
WINGS (1.2) 



31 



Taper and Twist 
(1.2.2.2.4) 



DRAG OF A WING-BODY CONFIGXJRATION CON- 
SISTING OF A SWEPT-FORWARD TAPERED WING 
MOUNTED ON A BODY OF FINENESS RATIO 12 
MEASURED DURING FREE FALL AT TRANSONIC 
SPEEDS. Jim Rogers Thompson and Charles W. 
Mathews. March 13, 1947. 15p. diagrs., photos. 
(NACA RM L6L24) 

DRAG MEASUREMENTS OF A SWEPT -BACK WING 
HAVING INVERSE TAPER AS DETERMINED BY 
FLIGHT TESTS AT SinJERSONIC SPEEDS. Sidney 
R. Alexander. April 8, 1947. 12p. diagrs., photo. 
(NACA RM L6L30) 

FLIGHT TESTS TO DETERMINE THE EFFECT OF 
TAPER ON THE ZERO-LIFT DRAG OF WINGS AT 
LOW SUPERSONIC SPEEDS. Sidney R. Alexander 
and Robert L. Nelson. July 13, 1947. 19p. diagrs., 
photos. (NACA RM L7E26) 

FLIGHT TESTS AT SUPERSONIC SPEEDS TO 
DETERMINE THE EFFECT OF TAPER ON THE 
ZERO-LIFT DRAG OF SWEPTBACK LOW-ASPECT- 
RATIO WINGS. Murray Pittel. September 5, 1950. 
23p. diagrs., photos. (NACA RM L50F30a) 

TRANSONIC DRAG CHARACTERISTICS OF A WING- 
BODY COMBINATION USING A THIN TAPERED 
WING OF 45° SWEEPBACK. Max C. Kurbjun and 
Stanley Faber. September 28, 1950. 14p. diagrs., 
photo., tab. (NACA RM L50H22) 

SMALL-SCALE INVESTIGATION AT TRANSONIC 
SPEEDS OF THE EFFECTS OF THICKENING THE 
INBOARD SECTION OF A 45° SWEPTBACK WING 
OF ASPECT RATIO 4, TAPER RATIO 0.3, AND 
NACA 65A006 AIRFOIL SECTION. Kenneth P. 
Spreemann and William J. Alford, Jr. August 1951. 
21p. diagrs., photo. (NACA RM L51F08a) 

INVESTIGATION OF THE LOW -SPEED AERODY- 
NAMIC CHARACTERISTICS OF A VARIABLE- 
SWEEP AIRPLANE MODEL WITH A TWISTED AND 
CAMBERED WING. William B. Kemp, Jr., Robert 
E. Becht and Albert G. Few, Jr. February 1952. 
62p. diagrs., photos. (NACA RM L51K22) 

THE INTERFERENCE EFFECTS OF A BODY ON 
THE SPANWISE LOAD DISTRIBUTIONS OF TWO 
45° SWEPTBACK WINGS OF ASPECT RATIO 8 
FROM LOW -SPEED TESTS AT A REYNOLDS 
NUMBER OF 4 X 10^. Albert P. Martina. February 
1952. 48p. diagrs., photo., 2 tabs. (NACA 
RM L51K23) 

INVESTIGATION OF THREE TAPERED 45° SWEPT- 
BACK CAMBERED AND TWISTED WINGS COVER- 
ING A SIMULTANEOUS VARIATION IN ASPECT 
RATIO AND THICKNESS RATIO AND OF ONE RE- 
LATED SYMMETRICAL WING AT TRANSONIC 
SPEEDS BY THE WING-FLOW METHOD. Harold I. 
Johnson. March 1953. 55p. diagrs., photos., 2 taba 
(NACA RM L52H07) 

LIFT AND PITCHING MOMENT AT SUPERSONIC 
SPEEDS DUE TO CONSTANT VERTICAL ACCELER- 
ATION FOR THIN SWEPTBACK TAPERED WINGS 
WITH STREAMWISE TIPS. SUPERSONIC LEADING 
AND TRAILING EDGES. Isabella J. Cole and 
Kenneth MargoUs. July 1954. 67p. diagrs., 4 tabs. 
(NACA TN 3196) 

THE ZERO-UFT WAVE DRAG OF A PARTICULAR 
FAMILY OF UNSWEPT, TAPERED WINGS WITH 
LINEARLY VARYING THICKNESS RATIO. Arthur 
Henderson, Jr. and Julia M. Goodwin. May 1955. 
28p. diagrs. (NACA TN 3418) 



Surface Conditions 
(1.2.2.2.6) 



EFFECT OF SWEEPBACK ON THE LOW -SPEED 
STATIC AND ROLLING STABILITY DERIVATIVES 
OF THIN TAPERED WINGS OF ASPECT RATIO 4. 
William Letlco and Walter D. Wolhart. August 9, 
1949. 36p. diagrs., photo. (NACA RM L9F14) 

THE EFFECT OF ASPECT RATIO ON THE SUB- 
SONIC AERODYNAMIC CHARACTERISTICS OF 
WINGS WITH NACA 65 1-210 SECTIONS. Warren H. 
Nelson and Albert L. Erickson. February 3, 1950. 
31p. diagrs., photos., tab. (NACA RM A9K18) 

AERODYNAMIC CHARACTERJBTICS WITH FIXED 
AND FREE TRANSITION OF A MODIFIED DELTA 
WING IN COMBINATION WITH A FUSELAGE AT 
HIGH SUBSONIC SPEEDS. Edward C. Polhamus and 
Thomas J. King, Jr. May 2, 1950. 19p. diagrs., 
photos. (NACA RM L50C21) 



AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBER OF 1.38 OF FOUR WiNGS OF ASPECT 
RATIO 4 HAVING QUARTER-CHORD SWEEP 
ANGLES OF 0°, 35°, 45°, AND 60°. WUliam B. 
Kemp, Jr., Kenneth W. Goodson and Robert A. Booth. 
October 10, 1950. 41p. diagrs., photos., tab. 
(NACA RM L50G14) 

THE EFFECTIVENESS OF WING VORTEX GENER- 
ATORS IN IMPROVING THE MANEUVERING CHAR- 
ACTERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, George 
A. Rathert, Jr. and Richard S. Bray. February 1952. 
45p. photos., diagrs., tab. (NACA RM A51J18) 

WIND-TUNNEL INVESTIGATION AT HIGH AND LOW 
SUBSONIC MACH NUMBERS OF A THIN SWEPT- 
BACK WING HAVING AN AIRFOIL SECTION DE- 
SIGNED FOR HIGH MAXIMUM ^.IFT. Stanley F. 
Racisz and Nicholas J. Paradiso. February 1952. 
46p. diagrs., photo., tab. (NACA RM L51L04) 

EFFECTS OF ROUGHNESS AND REYNOLDS NUM- 
BER ON THE NONLINEAR LIFT CHARACTERISTICS 
OF A WING WITH MODIFIED HEXAGONAL AIRFOIL 
SECTIONS. Milton A. Schwartzberg. 
February 1953. 18p. diagrs., photo. (NACA 
RM L52L26a) 

HOVERING PERFORMANCE OF A HELICOPTER 
ROTOR USING NACA 8-H-12 AIRFOIL SECTIONS. 
Robert D. Powell, Jr. August 1954. 14p. diagrs., 
photos. (NACA TN 3237) 



A PRELIMINARY FLIGHT INVESTIGATION OF AN 
OIL-FLOW TECHNIQUE FOR AIR-FLOW VISUALI- 
ZATION. Harold L Johnson and Robert G. Mungall. 
October 1954. 33p. diagrs., photos. (NACA 
RM L54G14a) 



Dihedral 



(1.2.2.2.7) 



EFFECT OF DIHEDRAL CHANGE ON THE THEO- 
RETICAL DYNAMIC LATERAL RESPONSE CHAR- 
ACTERISTICS OF A LOW-ASPECT-RATIO 
STRAIGHT -WING SUPERSONIC AIRPLANE. 
Donovan R. Heinle. December 7, 1950. 35p. diagrs., 
2 tabs. (NACA RM A50H02) 



AERODYNAMICS 
32 WINGS (1.2) 



HIGH- LIFT DEVICES 
(1.2.2o3) 

INVESTIGATION OF EFFECT OF SPAN AND 
SPANWBE LOCATION OF PLAIN AND STEPPED 
SPOILER AILERONS ON LATERAL CONTROL 
CHARACTERISTICS OF A WING WITH LEADING 
EDGE SWEPT BACK 51.3". Jack Fischei and 
Alexander D. Hammond. January 18, 1950. 59p. 
diagrs., photos. (NACA RM L9K02) 

THE INTERFERENCE EFFECTS OF A BODY ON 
THE SPANWISE LOAD DISTRIBUTIONS OF TWO 
45° SWEPTBACK WINGS OF ASPECT RATIO 8 
FROM LOW -SPEED TESTS AT A REYNOLDS 
NUMBER OF 4 X lO^. Albert P. Martina. February 
1952. 4Bp. diagrs., photo., 2 tabs. (NACA 
RM L51K23) 

METHOD FOR CALCULATING THE ROLLING AND 
YAWING MOMENTS DUE TO ROLLING FOR UN- 
SWEPT WINGS WITH OR WITHOUT FLAPS OR 
AILERONS BY USE OF NONLINEAR SECTION LIFT 
DATA. Albert P. Martina. 1954. ii, 16p. diagrs., 
11 tabs. (NACA Rept. 1167. Formerly TN 2937) 

DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A CASCADE-WING VERTICALLY RISING 
AIRPLANE MODEL IN TAKE-OFFS, LANDINGS, 
AND HOVERING FUGHT. Marion O. McKinney, 
Louis P. Tosti and Edwin E. Davenport. June 1954. 
45p. diagrs., photos., tab. (NACA TN 3198) 

INVESTIGATION OF THE AERODYNAMIC CHARAC- 
TERISTICS OF A MODEL WING-PROPELLER COM- 
BINATION AND OF THE WING AND PROPELLER 
SEPARATELY AT ANGLES OF ATTACK UP TO 90°. 
John W. Draper and Richard E. Kuhn. November 
1954. 72p. diagrs., photos., tab. (NACA TN 3304) 

AN INVESTIGATION OF A WING-PROPELLER CON- 
FIGURATION EMPLOYING LARGE -CHORD PLAIN 
FLAPS AND LARGE -DIAMETER PROPELLERS FOR 
LOW -SPEED FUGHT AND VERTICAL TAKE-OFF. 
Richard E. Kuhn and John W. Draper. December 

1954. 94p. diagrs., photos. (NACA TN 3307) 

SOME EFFECTS OF PROPELLER OPERATION AND 
LOCATION ON ABILITY OF A WING WITH PLAIN 
FLAPS TO DEFLECT PROPELLER SLIPSTREAMS 
DOWNWARD FOR VERTICAL TAKE-OFF. John W. 
Draper and Richard E. Kuhn. January 1955. 28p. 
diagrs., photo. (NACA TN 3360) 

INVESTIGATION OF EFFECTIVENESS OF LARGE - 
CHORD SLOTTED FLAPS IN DEFLECTING 
PROPELLER SLIPSTREAMS DOWNWARD FOR 
VERTICAL TAKE-OFF AND LOW -SPEED FLIGHT. 
Richard E. Kuhn and John W. Draper. January 

1955. 42p. diagrs., photo., tab. (NACA TN 3364) 

HOVERING FLIGHT TESTS OF A FOUR-ENGINE- 
TRANSPORT VERTICAL TAKE-OFF AIRPLANE 
MODEL UTILIZING A LARGE FLAP AND EXTEN- 
SIBLE VANES FOR REDIRECTING THE PROPEL- 
LER SLIPSTREAM. Louis P. Tosti and Edwin E. 
Davenport. May 1955. 26p. diagrs., photos., tab. 
(NACA TN 3440) 



Trailing-Edge Flaps 
(1.2.2.3.1) 



LANDING CHARACTERISTICS OF HIGH-SPEED 
WINGS. Herbert A. Wilson, Jr. and Laurence K. 
Lottin, Jr. September 21, 1948. 21p. diagrs. 
(NACA RM L8A28e) 



AN INVESTIGATION OF THE LOW-SPEED STATIC 
STABILITY CHARACTERISTICS OF COMPLETE 
MODELS HAVING SWEPTBACK AND SWEPT FOR- 
WARD WINGS. M. Leroy Spearman and Paul 
Comisarow. November 19, 1948. 51p. diagrs., tab. 
photos. (NACARM L8H31) 

THE AERODYNAMIC CHARACTERISTICS THROUGH- 
OUT THE SUBSONIC SPEED RANGE OF A THIN, 
SHARP -EDGED HORIZONTAL TAIL OF ASPECT 
RATIO 4 EQUIPPED WITH A CONSTANT -CHORD 
ELEVATOR. Angelo Bandettini and Verlin D. Reed. 
June 30, 1949. 50p. diagrs., photo. (NACA 
RM A9E05) 

INVESTIGATION OF EFFECT OF SPAN AND 
SPANWBE LOCATION OF PLAIN AND STEPPED 
SPOILER AILERONS ON LATERAL CONTROL 
CHARACTERISTICS OF A WING WITH LEADING 
EDGE SWEPT BACK 51.3°. Jack Fischei and 
Alexander D. Hammond. January 18, 1950. 59p. 
diagrs., photos. (NACA RM L9K02) 
THE TIME LAG BETWEEN FLAP DEFLECTION 
AND FORCE DEVELOPMENT AT A MACH NUMBER 
OF 4. Walter F. Lindsey and Edward F. Ulmann. 
February 13, 1950. lip. diagr., photos. (NACA 
RM L9L15) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LONGITiroiNAL STABILITY AND CON- 
TROL. William B. Kemp, Jr. Robert E. Becht and 
Albert G. Few, Jr. March 14, 1950. 51p. diagrs., 
photos. (NACA RM L9K08) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LATERAL AND DIRECTIONAL STABILITY 
AND CONTROL. William B. Kemp, Jr. and Robert 

E. Becht. June 20, 1950. 97p. diagrs., photos. 
(NACA RM L50C17a) 

LOW -SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AIRPLANE - LONGITUDINAL 
CHARACTERISTICS. Noel K. Delany and Nora-Lee 

F. Hayter. September 8, 1950. 80p. diagrs., 
photos., 2 tabs. (NACA RM A50G06) 

LOW -SPEED INVESTIGATION OF THE EFFECT OF 
SEVERAL FLAP AND SPOILER AILERONS ON THE 
LATERAL CHARACTERISTICS OF A 47.5° 
SWEPTBACK-WING - FUSELAGE COMBINATION 
AT A REYNOLDS NUMBER OF 4.4 x 10°. Jerome 
Pasamanick and Thomas B. Sellers. December 8, 
1950. 57p. diagrs., photo. (NACA RM L50J20) 

WIND-*rUNNEL INVESTIGATION AT MACH 
NUMBERS FROM 0.50 TO 1.29 OF AN UNSWEPT 
TAPERED WING OF ASPECT RATIO 2.67 WITH 
LEADING- AND TRAILING-EDGE FLAPS - 
TRAILING-EDGE FLAPS DEFLECTED. Louis S. 
Stivers, Jr. and Alexander W. Malick. 
December 13, 1950. 45p. diagrs., photo., 5 tabs. 
(NACA RM A50J09b). 

STABILITY AND CONTROL CHARACTERISTICS OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL IN 
THE LANDING CONFIGURATION. Robert E. Becht. 
December 18, 1950. 38p. diagrs., photos. (NACA 
RM L50J27) 

LOW-SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AIRPLANE - LATERAL AND 
DIRECTIONAL CHARACTERISTICS. Noel K. Delany 
and Nora-Lee F. Hayter. March 16, 1951. 56p. 
diagrs., photos., tab. (RM A51A16) 

EXPERIMENTAL DOWNWASH AND WAKE CHAR- 
ACTERISTICS AT SUBSONIC AND SUPERSONIC 
MACH NUMBERS BEHIND AN UNSWEPT, TAPERED 
WING OF ASPECT RATIO 2.67 WITH LEADING- 
AND TRAILING-EDGE FLAPS. Harold J. Walker, 
Louis S. Stivers, Jr. and Luther Beard, Jr. 
April 20, 1951. 43p. diagrs. (NACA RM A51B16) 



AERODYNAMICS 

WINGS (1.2). 3 3 



Tr ailing-Edge Flaps - Complete 
Wings (Cont. ) 

EFFECT OF A DEFLECTABLE WING-TIP CON- 
TROL ON THE LOW -SPEED LATERAL AND 
LONGITUDINAL CHARACTERISTICS OF A LARGE- 
SCALE WING WITH THE LEADING EDGE SWEPT 
BACK 47.5°. Roy H. Lange and Marvin P. Fink. 
April 26, 1951. 41p. dlagrs., photo., 2 tabs. 
(NACA RM L51C07) 

AERODYNAMIC CHARACTERISTICS AT TRAN- 
SONIC SPEEDS OF A TAPERED 45° SWEPTBACK 
WING OF ASPECT RATIO 3 HAVING A FULL-SPAN 
FLAP-TYPE CONTROL. TRANSONIC -BUMP 
METHOD. Vernard E. Lockwood and Joseph E. 
Flkes. August 1951. 35p. diagrs. (NACA 
RM L51F06a) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A TAPERED 45° SWEPTBACK WING 
OF ASPECT RATIO 3 HAVING A FULL-SPAN FLAP 
TYPE OF CONTROL WITH OVERHANG BALANCE. 
TRANSONIC -BUMP METHOD. Vernard E. 
Lockwood and John R. Hagerman. January 1952. 
24p. diagrs. (NACA RM L51L11) 

INVESTIGATION OF THE LOW-SPEED AERODY- 
NAMIC CHARACTERISTICS OF A VARIABLE- 
SWEEP AIRPLANE MODEL WITH A TWISTED AND 
CAMBERED WING. William B. Kemp, Jr., Robert 
E. Becht and Albert G. Few, Jr. February 1952. 
62p. diagrs., photos. (NACA RM L51K22) 

WIND-TUNNEL INVESTIGATION AT HIGH AND LOW 
SUBSONIC MACH NUMBERS OF A THIN SWEPT- 
BACK WING HAVING AN AIRFOIL SECTION DE- 
SIGNED FOR HIGH MAXIMUM LIFT. Stanley F. 
Racisz and Nicholas J. Paradiso. February 1952. 
46p. diagrs., photo., tab. (NACA RM L51L04) 

PRELIMINARY INVESTIGATION OF THE EFFECTS 
OF A PADDLE BALANCE ON THE CONTROL 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
TAPERED 45.58° SWEPTBACK WING OF ASPECT 
RATIO 3 HAVING A FULL-SPAN FLAP-TYPE CON- 
TROL. William C. Moseley, Jr. February 1952. 
24p. diagrs., photo. (NACA RM L51L19) 

FULL-SCALE WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF WING MODIFICATIONS AND 
HORIZONTAL-TAIL LOCATION ON THE LOW- 
SPEED STATIC LONGITUDINAL CHARACTERISTICS 
OF A 35° SWEPT -WING AIRPLANE. Ralph L. Maki. 
April 1952. 54p. diagrs., photos., 7 tabs. (NACA 
RM A52B05) 

PRELIMINARY INVESTIGATION OF CONTROL 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3 HAVING A HORN-BALANCED FULL-SPAN 
CONTROL. John G. Lowry and Joseph E. Fikes. 
April 1952. 22p. diagrs., photo. (NACA RM 
L52A11) I 

PRELIMINARY INVESTIGATION AT TRANSONIC 
SPEEDS OF THE EFFECT OF BALANCING TABS 
ON THE HINGE-MOMENT AND OTHER AERODY- 
NAMIC CHARACTERISTICS OF A FULL-SPAN FLAP 
ON A TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3. Vernard E. Lockwood and Joseph E. 
Fikes. April 1952. 27p. diagrs., photo., (NACA 
RM L52A23) 

CONTROL EFFECTIVENESS AND HINGE-MOMENT 
CHARACTERISTICS AT LOW SPEED OF LARGE- 
CHORD, HORN-BALANCED, FLAP-TYPE CON- 
TROLS ON A TRIANGULAR WING OF ASPECT 
RATIO 2. Jules B. Dods, Jr. August 1952. 53p. 
diagrs., photos., 2 tabs. (NACA RM A52F13) 



HINGE-MOMENT AND CONTROL-EFFECTIVENESS 
CHARACTERISTICS OF AN OUTBOARD FLAP WITH 
AN OVERHANG NOSE BALANCE ON A TAPERED 
35° SWEPTBACK WING OF ASPECT RATIO 4. 
TRANSONIC -BUMP METHOD. Robert F. Thompson 
and William C. Moseley, Jr. August 1952. 51p. 
diagrs. (NACA RM L52G08) 

THEORETICAL ANALYSES TO DETERMINE UN- 
BALANCED TRAILING-EDGE CONTROLS HAVING 
MINIMUM HINGE MOMENTS DUE TO DEFLECTION 
AT SUPERSONIC SPEEDS. Kennith L. Goin. 
November 1952. 52p. diagrs., tab. (NACA 
RM L51F19) 

CHARACTERISTICS OF FLAP-TYPE SPOILER 
AILERONS AT VARIOUS LOCATIONS ON A 60° 
DELTA WING WITH A DOUBLE SLOTTED FLAP. 
Delwin R. Croom. December 1952. 31p. diagrs., 
3 tabs. (NACA RM L52J24) 

A STUDY OF THE USE OF VARIOUS HIGH-LIFT DE- 
VICES ON THE HORIZONTAL TAIL OF A CANARD 
AIRPLANE MODEL AS A MEANS OF INCREASING 
THE ALLOWABLE CENTER-OF-GRAVITY 
TRAVEL. Joseph L. Johnson, Jr. January 1953. 
25p. diagrs., 2 tabs. (NACA RM L52K18a) 

EFFECTS OF RATE OF FLAP DEFLECTION ON 
FLAP HINGE MOMENT AND WING LIFT THROUGH 
THE MACH NUMBER RANGE FROM 0.32 TO 0.87. 
Thomas R. Turner. Jime 1953. 29p. diagrs., 
photos. (NACA RM L53E11) 

Slots and Slats 
(1.2„2. 3. 2) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LONGITUDINAL STABILITY AND CON- 
TROL. William B. Kemp, Jr. Robert E. Becht and 
Albert G. Few, Jr. March 14, 1950. 51p. diagrs., 
photos. (NACA RM L9K08) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LATERAL AND DIRECTIONAL STABILITY 
AND CONTROL. William B. Kemp, Jr. and Robert 
E. Becht. June 20, 1950. 97p. diagrs., photos. 
(NACA RM L50C17a) 

STABILITY AND CONTROL CHARACTERISTICS OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL IN 
THE LANDING CONFIGURATION. Robert E. Becht. 
December 18, 1950. 38p. diagrs., photos. (NACA 
RM L50J27) 

PRESSURE DISTRIBUTIONS OVER A RETRACTED 
LEADING-EDGE SLAT ON A 40° SWEPTBACK WING 
AT MACH NUMBERS UP TO 0.9. Jones F. Cahill 
and Gale C. Oberndorfer. January 26, 1951. 36p. 
diagrs. (NACA RM L50L04a) 

AERODYNAMIC CHAR.ACTERISTICS OF A 
LEADING-EDGE SLAT ON A 35° SWEPT-BACK 
WING FOR MACH NUMBERS FROM 0.30 TO 0.88. 
John A. Kelly and Nora-Lee F. Hayter. December 
1951. 49p. diagrs., tab. (NACA RM A51H23) 

PRESSURE DISTRIBUTION AT LOW SPEED ON A 
1/4-SCALE BELL X-5 AIRPLANE MODEL. 
William B. Kemp, Jr. and Albert G. Few, Jr. 
December 1951. 86p. diagrs., photos. (NACA 
RM L51I25) 

FULL-SCALE WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF WING MODIFICATIONS AND 
HORIZONTAL-TAIL LOCATION ON THE LOW- 
SPEED STATIC LONGITUDINAL CHARACTERISTICS 
OF A 35° SWEPT -WING AIRPLANE. Ralph L. Maki. 
April 1952. 54p. diagrs., photos., 7 tabs. (NACA 
RM A52B05) 



AERODYNAMICS 
34 WINGS (1. 2) 



Leading-Edge Flaps 
(1.2.2.3.3) 



EXPLORATORY INVESTIGATION OF LEADING- 
EDGE CHORD-EXTENSIONS TO IMPROVE THE 
LONGITUDINAL STABILITY CHARACTERISTICS OF 
TWO 52° SWEPTBACK WINGS. G. Chester Furlong. 
March 10, 1950. 32p. diagrs., photo. (NACA 
RM L50A30) 

LOW -SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AIRPLANE - LONGITUDINAL 
CHARACTERISTICS. Noel K, Delany and Nora-Lee 
F. Hayter. September 8, 1950. 80p. diagrs., 
photos., 2 tabs. (NACA RM A50G06) 

DAMPING IN YAW AND STATIC DIRECTIONAL 
STABILITY OF A CANARD AIRPLANE MODEL AND 
OF SEVERAL MODELS HAVING FUSELAGES OF 
RELATIVELY FLAT CROSS SECTION. Joseph L. 
Johnson. October 16, 1950. 20p. diagrs., tab. 
(NACA RM L50H30a) 

LOW -SPEED INVESTIGATION OF THE EFFECT OF 
SEVERAL FLAP AND SPOILER AILERONS ON THE 
LATERAL CHARACTERISTICS OF A 47.5° 
SWEPTBACK-WING - FUSELAGE COMBINATION 
AT A REYNOLDS NUMBER OF 4.4 x 10^. Jerome 
Pasamanick and Thomas B. Sellers. December 8, 

1950. 57p. diagrs., photo. (NACA RM L50J20) 

WIND-TUNNEL INVESTIGATION AT MACH NUM- 
BERS FROM 0.50 TO 1.29 OF AN UNSWEPT, 
TAPERED WING OF ASPECT RATIO 2.67 WITH 
LEADING- AND TRAIUNG-EDGE FLAPS - 
LEADING-EDGE FLAPS DEFLECTED. Louis S. 
Stivers, Jr. and Alexander W. Mallck. February 26, 

1951. 37p. diagrs., photo., 5 tabs. (NACA 
RM A50K10) 

LOW -SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AIRPLANE - LATERAL AND 
DfflECTIONAL CHARACTERISTICS. Noel K. Delany 
and Nora-Lee F. Hayter. March 16, 1951. 56p. 
diagrs., photos., tab. (RM A51A16) 

EXPERIMENTAL DOWNWASH AND WAKE CHAR- 
ACTERISTICS AT SUBSONIC AND SUPERSONIC 
MACH NUMBERS BEHIND AN UNSWEPT, TAPERED 
WING OF ASPECT RATIO 2.67 WITH LEADING- 
AND TRAILING-EDGE FLAPS. Harold J. Walker, 
Louis S. Stivers, Jr. and Luther Beard, Jr. 
April 20, 1951. 43p. diagrs. (NACA RM A51B16) 

EFFECT OF A DEFLECTABLE WING-TIP CON- 
TROL ON THE LOW -SPEED LATERAL AND 
LONGITUDINAL CHARACTERISTICS OF A LARGE- 
SCALE WING WITH THE LEADING EDGE SWEPT 
BACK 47.5°. Roy H. Lange and Marvin P. Fink. 
April 26, 1951. 41p. diagrs., photo., 2 tabs. 
{NACA RM L51C07) 

SMALL-SCALE TRANSONIC INVESTIGATION OF 
THE EFFECTS OF FULL-SPAN AND PARTIAL- 
SPAN LEADING-EDGE FLAPS ON THE AERO- 
DYNAMIC CHARACTERISTICS OF A 50° 38' SWEPT- 
BACK WING OF ASPECT RATIO 2.98. Kenneth P. 
Spreeraann and William J. Alford, Jr. July 1952. 
31p. diagrs., photo. (NACA RM L52E12) 

A STUDY OF THE USE OF VARIOUS HIGH-LIFT DE- 
VICES ON THE HORIZONTAL TAIL OF A CANARD 
AIRPLANE MODEL AS A MEANS OF INCREASING 
THE ALLOWABLE CENTER-OF-GRAVITY 
TRAVEL. Joseph L. Johnson, Jr. January 1953. 
25p. diagrs., 2 tabs. (NACA RM L52K18a) 

FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW -SPEED STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A MODEL HAVING A FUSELAGE 
OR RE LATIVELY FLAT CROSS SECTION. John W. 
Paulson and Joseph L. Johnson, Jr. February 1953. 
30p. diagrs., photo., tab. (NACA RM L52L22) 



CONTROLS 
(1.2.2.4) 

FREE-FLIGHT INVESTIGATION OF THE ROLLING 
EFFECTIVENESS OF A WING-SPOILER ARRANGE- 
MENT AT HIGH SUBSONIC, TRANSONIC, AND 
SUPERSONIC SPEEDS. Carl A. SandahL May 17, 
1948. lOp. diagrs., photo. (NACA RM L8A07) 

INVESTIGATION OF EXTENSIBLE WING-TIP 
AILEROie ON AN UNTAPERED SEMBPAN WING 
AT 0° AND 45° SWEEPBACK. John R. Hagennan 
and William M. O'Hare. September 20, 1949. 40p. 
diagrs., photo., tab. (NACA RM L9H04) 

LOW -SPEED INVESTIGATION OF DEFLECTABLE 
WING-TIP AILERONS ON AN UNTAPERED 45° 
SWEPTBACK SEMISPAN WING WITH AND WITHOUT 
AN END PLATE. Jack Fischel and James M. 
Watson. December 14, 1949. 32p. diagrs., photo. 
(NACA RM L9J28) 

INVESTIGATION OF WING-TIP AILERONS ON A 
51.3° SWEPTBACK WING AT TRANSONIC SPEEDS 
BY THE TRANSONIC -BUMP METHOD. William C. 
Moseley, Jr. and James M. Watson. November 1951. 
60p. diagrs. (NACA RM L51H27) 

LOW-SPEED WIND-TUNNEL INVESTIGATION OF A 
FDCED AND A FREE-FLOATING WING-TIP AILER- 
ON ON A WING WITH LEADING EDGE SWEPT 
BACK 51.3°. R. G. MacLeod. February 1952. 
17p. diagrs., photo., tab. (NACA RM L51H 16a) 

METHOD FOR CALCULATING THE ROLLING AND 
YAWING MOMENTS DUE TO ROLLING FOR UN- 
SWEPT WINGS WITH OR WITHOUT FLAPS OR 
AILERONS BY USE OF NONLINEAR SECTION LIFT 
DATA. Albert P. Martina. 1954. ii, 16p. diagrs., 
11 tabs. (NACA Rept. 1167. Formerly TN 2937) 



Flap Type 
(1.2.2.4. 1) 



OBSERVATIONS ON AN AILERON-FLUTTER IN- 
STABILITY ENCOUNTERED ON A 45° SWEPT- 
BACK WING IN TRANSONIC AND SUPERSONIC 
FLIGHT. Marvin Pitkin, William N. Gardner and 
Howard J. Curfman, Jr. April 11, 1947. 23p. 
diagrs., photos. (NACA RM L6L09) 

FLIGHT -TEST MEASUREMENTS OF AILERON CON- 
TROL SURFACE BEHAVIOUR AT SUPERCRITICAL 
MACH NUMBERS. Harvey H. Brown, George A. 
Rathert, Jr. and Lawrence A. Clousing. April 23, 
1947. 26p. diagrs., photos., 2 tabs. (NACA 
RM A7A15) 

HIGH-SPEED WIND-TUNNEL TESTS OF A MODEL 
PURSUIT AIRPLANE AND CORRELATION WITH 
FLIGHT-TEST RESULTS. Joseph W. Cleary and 
Lyle J. Gray. January 21, 1948. 56p. diagrs., 
photos. (NACA RM A7I16) 

WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 1.53 OF AN AIRPLANE WITH A TRIANGU- 
LAR WING. Richard Scherrer and William R. 
Wimbrow. January 23, 1948. 74p. diagrs., 
photos., 2 tabs. (NACA RM A7J05) 



QUALITATIVE MEASUREMENTS OF RELATIVE 
FLAP EFFECTIVENESS AT TRANSONIC SPEEDS 
ON A SERIES OF FIVE THIN AIRFOILS WITH 25- 
PERCENT-CHORD FLAPS AND VARIOUS AMOUNTS 
OF SWEEPBACK. Harold L. Crane and Milton D. 
McLaughlin. May 17, 1948. 24p. diagrs., photos. 
(NACA RM L8A22) 



AERODYNAMICS 
WINGS (1.2) 



35 



Flap Type Controls - Complete 
Wings (Cont. ) 

PRELIMINARY FREE-FUGHT INVESTIGATION OF 
THE EFFECT OF AIRFOIL SECTION ON AILERON 
ROLLING EFFECTIVENESS AT TRANSONIC AND 
SUPERSONIC SPEEDS. Carl A. Sandahl. June 25, 
1948. 6p. diagrs. (NACA RM L8B26) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
WITH A SWEPTBACK WING AND TAIL FROM 
TESTS AT TRANSONIC SPEEDS BY THE NACA 
WING-FLOW METHOD. Richard H. Sawyer and 
Lindsay J. Llna. July 23, 1948. 42p. diagrs., 
photos., tab. (NACA RM L8B19) 

ADDITIONAL FREE-FUGHT TESTS OF THE ROLL- 
ING EFFECTIVENESS OF SEVERAL WING-SPOILER 
ARRANGEMENTS AT HIGH SUBSONIC, TRANSONIC, 
AND SUPERSONIC SPEEDS. H. Kurt Strass. 
November 24, 1948. 16p. diagrs., photos. (NACA 
RM L8I23) 

AN INVESTIGATION OF AILERON OSCILLATIONS 
AT TRANSONIC SPEEDS ON NACA 23012 AND 
NACA 65-212 AIRFOILS BY THE WING-FLOW 
METHOD. Harold L. Crane. December 29, 1948. 
9p. diagrs., photo. (NACA RM L8K29) 

AERODYNAMIC CHARACTERISTICS AT SUBSONIC 
AND TRANSONIC SPEEDS OF A 4,2.7° SWEPTBACK 
WING MODEL HAVING AN AILERGN WITH FINITE 
TRAILING-EDGE THICKNESS. Thomas R. Turner, 
Vernard E. Lockwood and Raymond D. Vogler. 
January 12, 1949. 24p. diagrs., photo. (NACA 
RM L8K02) 

FULL-SCALE INVESTIGATION OF A WING WITH 
THE LEADING EDGE SWEPT BACK 47. 5° AND 
HAVING CIRCULAR-ARC AND FINITE -TRAILING- 
EDGE -THICKNESS AILERONS. Roy H. Lange. 
March 11, 1949. 16p. diagrs., photo. (NACA 
RM L9B02) 

MEASUREMENTS OF AERODYNAMIC CHARACTER- 
ISTICS OF A 35° SWEPTBACK NACA 65-009 AIR- 
FOIL MODEL WITH 1/4-CHORD HORN-BALANCED 
FLAP BY THE NACA WING-FLOW METHOD. 
Harold I. Johnson and B. Porter Brown. April 18, 
1949. 59p. diagrs., photo. (NACA RM L9B23a) 

WIND-TUNNEL INVESTIGATION AT HIGH SUB- 
SONIC SPEEDS OF THE LATERAL-CONTROL 
CHARACTERISTICS OF AN AILERON AND A 
STEPPED SPOILER ON A WING WITH LEADING 
EDGE SWEPT BACK 51.3°. Leslie E. Schneiter 
and John R. Hagerman. June 7, 1949. 34p. diagrs., 
photo. (NACA RM L9D06) 

EFFECTS OF MACH NUMBER AND SWEEP ON THE 
DAMPING-IN-ROLL CHARACTERISTICS OF WINGS 
OF ASPECT RATIO 4. Richard E. Kuhn and Boyd 

C. Myers, II. June 27, 1949. 28p. diagrs., photo. 
(NACA RM L9E10) 

THE AERODYNAMIC CHARACTERISTICS THROUGH- 
OUT THE SUBSONIC SPEED RANGE OF A THIN, 
SHARP-EDGED HORIZONTAL TAIL OF ASPECT 
RATIO 4 EQUIPPED WITH A CONSTANT -CHORD 
ELEVATOR. Angelo Bandettini and Verlin D. Reed. 
June 30, 1949. 50p. diagrs., photo. (NACA 
RM A9E05) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER - 
CHORD LINE SWEPT BACK 45°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. Raymond 

D. Vogler. August 15, 1949. 22p. diagrs. (NACA 
RM L9F29a) 



WIND-TUNNEL INVESTIGATION AT LOW TRAN- 
SONIC SPEEES OF THE EFFECTS OF NUMBER OF 
WINGS ON THE LATERAL-CONTROL EFFECTIVE- 
NESS OF AN RM-5 TEST VEHICLE. Harold S. 
Johnson. November 29, 1949. 15p. diagrs., photo., 
tab. (NACA RM L9H16) 

MEASUREMENTS OF AERODYNAMIC CHARACTER- 
ISTICS OF A 35° SWEPTBACK NACA 65-009 AIR- 
FOIL MODEL WITH 1/4-CHORD BEVELLED- 
TRAILING-EDGE FLAP AND TRIM TAB BY THE 
NACA WING-FLOW METHOD. Harold I. Johnson 
and B. Porter Brown. January 6, 1950. 68p. 
diagrs., photo. (NACA RM L9K11) 

THE EFFECT OF TIP TANKS ON THE ROLLING 
CHARACTERISTICS AT HIGH SUBSONIC MACH 
NUMBERS OF A WING HAVING AN ASPECT RATIO 
OF 3 WITH QUARTER-CHORD LINE SWEPT BACK 
35°. Richard E. Kuhn and Boyd C. Myers, n. 
January 17, 1950. 27p. diagrs., photo., 2 tabs. 
(NACA RM L9J19) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER - 
CHORD LINE SWEPT BACK 35°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. Robert F. 
Thompson. January 25, 1950. 22p. diagrs., tab. 
(NACA RM L9L12a) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER- 
CHORD LINE SWEPT BACK 60°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC-BUMP METHOD. Raymond 
D. Vogler. March 2, 1950. 21p. diagrs. (NACA 
RM L50A17) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH UNSWEPT 
QUARTER-CHORD LINE, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. 
Alexander D. Hammond. March 10, 1950. 20p. 
diagrs. (NACA RM L50A03) 

INVESTIGATION AT HIGH SUBSONIC SPEEDS OF A 
45° SWEPTBACK HORIZONTAL TAIL WITH PLAIN 
AND HORN-BALANCED CONTROL SURFACES. 
Harold S. Johnson and Robert F. Thompson. 
March 31, 1950. 44p. diagrs., photo., tab. (NACA 
RM L50B13) 

FLIGHT INVESTIGATION OF THE EFFECT OF 
THICKENING THE AILERON TRAILING EDGE ON 
CONTROL EFFECTIVENESS FOR SWEPTBACK 
TAPERED WINGS HAVING SHARP- AND ROUND- 
NOSE SECTIONS. H. Kurt Strass and Edison M. 
Fields. May 2, 1950. 20p. diagrs., photo., tab. 
(NACA RM L9L19) 

AERODYNAMIC AND LATERAL-CONTROL CHAR- 
ACTERISTICS OF A 1/28-SCALE MODEL OF THE 
BELL X-1 AIRPLANE WING-FUSELAGE COMBINA- 
TION. TRANSONIC-BUMP METHOD. Vernard E. 
Lockwood. May 5, 1950. 28p. diagrs., tab. (NACA 
RM L50C22) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE AND SPOILER-TYPE CONTROLS ON A WING 
WITH QUARTER -CHORD-LINE SWEEPBACK OF 
60°, ASPECT RATIO 2, TAPER RATIO 0.6, AND 
NACA 65A006 AIRFOIL SECTION. TRANSONIC - 
BUMP METHOD. Alexander D. Hammond. July 18, 
1950. 26p. diagrs. (NACA RM L50E09) 



AERODYNAMICS 
36 WINGS (1. 2) 



Flap Type Controls - Complete 
Wings (Cont. ) 

INVESTIGATION OF FLAP-TYPE AILERONS ON AN 
UNTAPERED VWNG HAVING AN ASPECT RATIO OF 
3.7, 45° SWEEPBACK, AND AN NACA 65A009 AIR- 
FOIL SECTION. TRANSONIC-BUMP METHOD. 
Richard G. MacLeod. August 23, 1950. 18p. 
diagrs. (NACA RM L50GO3) 

INVESTIGATION AT TRANSONIC SPEEDS OF A 
35-PERCENT-CHORD AILERON ON A TAPERED 
WEDGE-TYPE WING OF ASPECT RATIO 2.5 WITH 
AND WITHOUT A FUSELAGE. Thomas R. Turner 
and Joseph E. Flkes. September 8, 1950. 25p. 
diagrs. (NACA RM L50G13a) 

PRELIMINARY FLIGHT INVESTIGATION OF THE 
WING-DROPPING TENDENCY AND LATERAL- 
CONTROL CHARACTERISTICS OF A 35° SWEPT- 
WING AIRPLANE AT TRANSONIC MACH NUMBERS. 
George A. Rathert, Jr. , L. Stewart Rolls, Lee 
Winograd and George E. Cooper. September 11, 
1950. 14p. diagrs., photo., tab. (NACA RM A50H03) 

MEASUREMENTS OF AERODYNAMIC CHARACTER- 
ISTICS OF A 35° SWEPTBACK NACA 65-009 AIR- 
FOIL MODEL WITH 1/4-CHORD FLAP HAVING A 
31 -PERCENT -FLAP -CHORD OVERHANG BALANCE 
BY THE NACA WING-FLOW METHOD. Harold I. 
Johnson and Harold R. Goodman. September 25, 
1950. 38p. diagrs., photo. (NACA RM L50H09) 

LOW-SPEED INVESTIGATION OF THE EFFECT OF 
SEVERAL FLAP AND SPOILER AILERONS ON THE 
LATERAL CHARACTERISTICS OF A 47.5° 
SWEPTBACK-WING - FUSELAGE COMBINATION 
AT A REYNOLDS NUMBER OF 4.4 X 10^. Jerome 
Pasamanick and Thomas B; Sellers. December 8, 

1950. 57p. diagrs., photo. (NACA RM L50J20) 

WIND-TUNNEL INVESTIGATION AT MACH 
NUMBERS FROM 0.50 TO 1.29 OF AN UNSWEPT 
TAPERED WING OF ASPECT RATIO 2.67 WITH 
LEADING- AND TRAILING-EDGE FLAPS - 
TRAILING-EDGE FLAPS DEFLECTED. Louis S. 
Stivers, Jr. and Alexander W. Malick. 
December 13, 1950. 45p. diagrs., photo., 5 tabs. 
(NACA RM A50J09b) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 60° DELTA WING EQUIPPED WITH A 
TRIANGULAR PLAN-FORM CONTROL HAVING A 
SKEWED HINGE AXIS AND AN OVERHANG BAL- 
ANCE. TRANSONIC -BUMP METHOD. Harleth G. 
Wiley. February 6, 1951. 31p. diagrs. (NACA 
RM L50L01) 

WIND-TUNNEL INVESTIGATION AT MACH NUM- 
BERS FROM 0.50 TO 1.29 OF AN UNSWEPT, 
TAPERED WING OF ASPECT RATIO 2.67 WITH 
LEADING- AND TRAILING-EDGE FLAPS - 
LEADING-EDGE FLAPS DEFLECTED. Louis S. 
Stivers, Jr. and Alexander W. Mallck. February 26, 

1951. 37p. dUgrs., photo., 5 tabs. (NACA 
RM A50K10) 

FLIGHT MEASUREMENTS OF THE WING- 
DROPPING TENDENCY OF A STRAIGHT -WING JET 
AIRPLANE AT HIGH SUBSONIC MACH NUMBERS. 
Seth B. Anderson, Edward A. Ernst and Rudolph D. 
Van Dyke, Jr. April 24, 1951. 16p. diagrs., photo., 
tab. (NACA RM A51B28) 

EFFECT OF A DEFLECTABLE WING-TIP CON- 
TROL ON THE LOW -SPEED LATERAL AND 
LONGITUDINAL CHARACTERISTICS OF A LARGE- 
SCALE WING WITH THE LEADING EDGE SWEPT 
BACK 47.5°. Roy H. Lange and Marvin P. Fink. 
April 26, 1951. 41p. diagrs., photo., 2 tabs. 
(NACA RM L51C07) 



AERODYNAMIC CHARACTERISTICS AT TRAN- 
SONIC SPEEDS OF A TAPERED 45° SWEPTBACK 
WING OF ASPECT RATIO 3 HAVING A FULL-SPAN 
FLAP -TYPE CONTROL. TRANSONIC -BUMP 
METHOD. Vernard E. Lockwood and Joseph E. 
Fikes. August 1951. 35p. diagrs. (NACA 
RM L51F06a) 

AN INVESTIGATION AT TRANSONIC SPEEDS OF 
THE EFFECTS OF CONTROL CHORD AND SPAN 
ON THE CONTROL CHARACTERISTICS OF A 
TAPERED WEDGE-TYPE WING OF ASPECT RATIO 
2.5. TRANSONIC -BUMP METHOD. Raymond D. 
Vogler, Vernard E. Lockwood and Thomas R. 
Turner. September 1951. 36p. diagrs. (NACA 
RM L51G03) 

THE EFFECT OF RAKING THE AILERON TIPS ON 
THE LATERAL -CONTROL AND HINGE -MOMENT 
CHAJRACTERISTICS OF A 20-PERCENT -CHORD 
PARTIAL-SPAN OUTBOARD AILERON ON A WING 
WITH LEADING EDGE SWEPT BACK 51.3°. 
Alexander D. Hammond. November 1951. 41p. 
diagrs., photo., tab. (NACA RM L51H29) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A TAPERED 45° SWEPTBACK WING 
OF ASPECT RATIO 3 HAVING A FULL-SPAN FLAP 
TYPE OF CONTROL WITH OVERHANG BALANCE. 
TRANSONIC -BUMP METHOD. Vernard E. 
Lockwood and John R. Hagerman. January 1952. 
24p. diagrs. (NACA RM L51L11) 

PRELIMINARY INVESTIGATION OF THE EFFECTS 
OF A PADDLE BALANCE ON THE CONTROL 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
TAPERED 45.58° SWEPTBACK WING OF ASPECT 
RATIO 3 HAVING A FULL-SPAN FLAP-TYPE CON- 
TROL. William C. Moseley, Jr. February 1952. 
24p. diagrs., photo. (NACA RM L51L19) 

PRELIMINARY INVESTIGATION OF CONTROL 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3 HAVING A HORN-BALANCED FULL-SPAN 
CONTROL. John G. Loi^ry and Joseph E. Fikes. 
April 1952. 22p. diagrs., photo. (NACA RM 
L52A11) 



PRELIMINARY INVESTIGATION AT TRANSONIC 
SPEEDS OF THE EFFECT OF BALANCING TABS 
ON THE HINGE-MOMENT AND OTHER AERODY- 
NAMIC CHARACTERISTICS OF A FULL-SPAN FLAP 
ON A TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3. Vernard E. Lockwood and Joseph E. 
Fikes. April 1952. 27p. diagrs., photo., (NACA 
RM L52A23) 

AN ANALYSIS OF THE EFFECT OF STRUCTURAL 
FEEDBACK ON THE FLUTTER OF A CONTROL 
SURFACE HAVING POWER -BOOST SYSTEM. 
Robert H. Barnes. June 1952. 29p. diagrs., photos. 
(NACA RM A51I25) 

CONTROL EFFECTIVENESS AND HINGE-MOMENT 
CHARACTERISTICS AT LOW SPEED OF LARGE- 
CHORD, HORN-BALANCED, FLAP-TYPE CON- 
TROLS ON A TRIANGULAR WING OF ASPECT 
RATIO 2. Jules B. Dods, Jr. August 1952. 53p. 
diagrs., photos., 2 tabs. (NACA RM A52F13) 

HINGE-MOMENT AND CONTROL-EFFECTIVENESS 
CHARACTERISTICS OF AN OUTBOARD FLAP WITH 
AN OVERHANG NOSE BALANCE ON A TAPERED 
35° SWEPTBACK WING OF ASPECT RATIO 4. 
TRANSONIC-BUMP METHOD. Robert F. Thompson 
and William C. Moseley, Jr. August 1952. 51p. 
diagrs. (NACA RM L52G08) 



AERODYNAMICS 
WINGS (1. 2) 



37 



Flap Type Controls - Complete 
Wings (Cont. ) 

AERODYNAMiC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 60° DELTA WING EQUIPPED WITH A 
CONSTANT -CHORD FLAP-TYPE CONTROL WITH 
AND WITHOirr AN UNSHIELDED HORN BALANCE. 
TRANSONIC -BUMP METHOD. Harleth G. Wiley 
and Leon Zontek. September 1952. 25p. diagrs. 
(NACA RM L51H22) 

THE EFF.ECT OF VARIOUS AERODYNAMIC BAL- 
ANCES ON THE LOW -SPEED LATERAL-CONTROL 
AND HINGE-MOMENT CHARACTERISTICS OF A 
0.20-CHORD PARTIAL-SPAN OUTBOARD AILERON 
ON A WING WITH LEADING EDGE SWEPT BACK 
51.3°. Alexander D. Hammond. September 1952. 
40 p. diagrs., photo., tab. (NACA RM L52G03) 

THEORETICAL ANALYSES TO DETERMINE UN- 
BALANCED TRAILING-EDGE CONTROLS HAVING 
MINIMUM HINGE MOMENTS DUE TO DEFLECTION 
AT SUPERSONIC SPEEDS. Kennith L. Goin. 
November 1952. 52p. diagrs., tab. (NACA 
RM L51F19) 

INVESTIGATION AT TRANSONIC SPEEDS OF THE 
EFFECT OF A POSITIVE-LIFT BALANCING TAB 
ON THE HINGE-MOMENT AND LIFT CHARACTER- 
ISTICS OF A FULL-SPAN FLAP ON A TAPERED 
45° SWEPTBACK WING OF ASPECT RATIO 3. 
Vernard E. Lockwood and Joseph E. Fikes. 
November 1952. 22p. diagrs. , photo. (NACA 
RM L52J09) 

MEASUREMENTS OF AERODYNAMIC CHAR- 
ACTERISTICS AT TRANSONIC SPEEDS OF AN 
UNSWEPT AND UNTAPERED NACA 65-009 AIR- 
FOIL MODEL OF ASPECT RATIO 3 WITH 1/4- 
CHORD PLAIN FLAP BY THE NACA WING-FLOW 
METHOD. Harold I. Johnson. June 1953. 35p. 
diagrs., photo. (NACA RM L53D21) 

EFFECTS OF RATE OF FLAP DEFLECTION ON 
FLAP HINGE MOMENT AND WING LIFT THROUGH 
THE MACH NUMBER RANGE FROM 0.32 TO 0.87. 
Thomas R. Turner. June 1953. 29p. diagrs., 
photos. (NACA RM L53E11) 

INVESTIGATION AT TRANSONIC SPEEDS OF THE 
HINGE-MOMENT AND LIFT-EFFECTIVENESS 
CHARACTERISTICS OF A SINGLE FLAP AND A 
TANDEM FLAP ON A 60° DELTA WING. Delwin 
R. Croom and Harleth G. Wiley. July 1953. 16p. 
diagrs. (NACA RM L53E28a) 



Spoil 



ers 



(1.2.2.4.2) 

FREE-FLIGHT INVESTIGATION OF THE ROLLING 
EFFECTIVENESS OF A WING-SPOILER ARRANGE- 
MENT AT HIGH SUBSONIC, TRANSONIC, AND 
SUPERSONIC SPEEDS. Carl A. Sandahl. May 17, 
1948. lOp. diagrs., photo. (NACA RM L8A07) 

ADDITIONAL FREE-FLIGHT TESTS OF THE ROLL- 
ING EFFECTIVENESS OF SEVERAL WING-SPOILER 
ARRANGEMENTS AT HIGH SUBSONIC, TRANSONIC, 
AND SUPERSONIC SPEEDS. H. Kurt Strass. 
November 24, 1948. 16p. diagrs., photos. (NACA 
RM L8I23) 

WIND-TUNNEL INVESTIGATION AT HIGH SUB- 
SONIC SPEEDS OF THE LATERAL-CONTROL 
CHARACTERISTICS OF AN AILERON AND A 
STEPPED SPOILER ON A WING WITH LEADING 
EDGE SWEPT BACK 51.3°. Leslie E. Schneiter 
and John R. Hagerman. June 7, 1949. 34p. diagrs., 
photo. (NACA RM L9D06) 



INVESTIGATION OF EFFECT OF SPAN AND 
SPANWDSE LOCATION OF PLAIN AND STEPPED 
SPOILER AILERONS ON LATERAL CONTROL 
CHARACTERISTICS OF A WING WITH LEADING 
EDGE SWEPT BACK 51.3°. Jack Fischel and 
Alexander D. Hammond. January 18, 1950. 59p. 
diagrs., photos. (NACA RM L9K02) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE AND SPOILER-TYPE CONTROLS ON A WING 
WITH QUARTER -CHORD-LINE SWEEPBACK OF 
60°, ASPECT RATIO 2, TAPER RATIO 0.6, AND 
NACA 65A006 AIRFOIL SECTION. TRANSONIC- 
BUMP METHOD. Alexander D. Hammond. July 18, 
1950. 26p. diagrs. (NACA RM L50E09) 

LOW -SPEED INVESTIGATION OF THE EFFECT OF 
SEVERAL FLAP AND SPOILER AILERONS ON THE 
LATERAL CHARACTERISTICS OF A 47.5° 
SWEPTBACK-WING - FUSELAGE COMBINATION 
AT A REYNOLDS NUMBER OF 4.4 X 10^. Jerome 
Pasamanick and Thomas B. Sellers. December 8, 
1950. 57p. diagrs., photo. (NACA RM L50J20) 

HINGE -MOMENT AND OTHER AERODYNAMIC 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
QUARTER-SPAN SPOILER ON A TAPERED 45° 
SWEPTBACK WING OF ASPECT RATIO 3. 
Joseph E. Fikes. February 1952. 22p. diagrs., 
photo. (NACA RM L52A03) 

CONTROL CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A LINKED FLAP AND SPOILER ON A 
TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIOS. Vernard E. Lockwood and Joseph E. 
Fikes. July 1952. 24p. diagrs., photo. (NACA 
RM L52D25) 

LATERAL-CONTROL INVESTIGATION AT TRAN- 
SONIC SPEEDS OF RETRACTABLE SPOILER AND 
PLUG-TYPE SPOILER-SLOT AILERONS ON A 
TAPERED 60° SWEPTBACK WING OF ASPECT 
RATIO 2. TRANSONIC -BUMP METHOD. Alexander 
D. Hammond and James M. Watson. August 1952. 
19p. diagrs. (NACA RM L52F16) 

LOW -SPEED LATERAL-CONTROL INVESTIGATION 
OF A FLAP -TYPE SPOILER AILERON WITH AND 
WITHOUT A DEFLECTOR AND SLOT ON A 6- 
PERCENT-THICK, TAPEREfa, 45° SWEPTBACK 
WING OF ASPECT RATIO 4. James M. Watson. 
September 1952. Up. diagrs. (NACA RM L52G10) 

A WIND-TUNNEL INVESTIGATION AT LOW 
SPEEDS OF THE AERODYNAMIC CHARACTER- 
ISTICS OF VARIOUS SPOILER CONFIGURATIONS 
ON A THIN 60° DELTA WING. Harleth G. Wiley 
and Martin Solomon. November 1952. 20p. diagrs. 
(NACA RM L52J13) 

CHARACTERISTICS OF FLAP -TYPE SPOILER 
AILERONS AT VARIOUS LOCATIONS ON A 60° 
■DELTA WING WITH A DOUBLE SLOTTED FLAP. 
Delwin R. Croom. December 1952. 31p. diagrs., 
3 tabs. (NACA RM L52J24) 

All Movable 
(1.2.2.4.3) 

WIND-TUNNEL INVESTIGATIQN AT MACH NUM- 
BERS FROM 0.50 TO 1.20 OF AN ALL-MOVABLE 
TRIANGULAR WING OF ASPECT RATIO 4 ALONE 
AND WITH A BODY. Louis S. Stivers, Jr. and 
Alexander W. Malick. February 2, 1950. 45p. 
diagrs., photos., tab. (NACA RM A9L01) 

LOW -SPEED INVESTIGATION OF DEFLECTABLE 
WING-TIP ELEVATORS ON A LOW -ASPECT -RATIO 
UNTAPERED 45° SWEPTBACK SEMISPAN WING 
WITH AND WITHOUT AN END PLATE. Jack 
Fischel and William M. O'Hare. June 1, 1950. 21p. 
diagrs., photo. (NACA RM L50D19) 



AERODYNAMICS 
38 WINGS (1.2) 



All-Movable Controls - Complete 
Wings (Cont. ) 

EFFECT OF A DEFLECTABLE WING-TtP CON- 
TROL ON THE LOW-SPEED LATERAL AND 
LONGITUDINAL CHARACTERISTICS OF A LARGE- 
SCALE WING WITH THE LEADING EDGE SWEPT 
BACK 47.5°. Roy H. Lange and Marvin P. Fink. 
April 26, 1951. 41p. diagrs., photo., 2 tabs. 
(NACA RM L51C07) 

EFFECTS OF HORIZONTAL-TAIL POSITION, AREA, 
AND ASPECT RATIO ON LOW -SPEED STATIC 
LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A 60° TRIANGULAR-WING 
MODEL HAVING VARIOUS TRIANGULAR-ALL- 
MOVABLE HORIZONTAL TAILS. Byron M. Jaquet. 
December 1951. 61p. diagrs., photo., tab. (NACA 
RM L51I06) 

LOW -SPEED STATIC LONGITUDINAL STABILITY 
AND CONTROL CHARACTERISTICS OF 60° 
TRIANGULAR-WING AND MODIFIED 60° 
TRIANGULAR -WING MODELS HAVING HALF- 
DELTA AND HALF-DIAMOND TIP CONTROLS. 
Jacob H. Lichtenstein and Byron M. Jaquet. 
February 1952. 36p. diagrs., photos., tab. (NACA 
RM L51K08) 

EFFECTS OF HORIZONTAL -TAIL POSITION AND 
ASPECT RATIO ON LOW -SPEED STATIC LONGI- 
TUDINAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF A 60° TRIANGULAR -WING MODEL HAV- 
ING TWIN TRIANGULAR ALL-MOVABLE TAILS. 
Byron M. Jaquet. May 1952. 45p. diagrs., photos. 
(NACA RM L52B25) 

AN INVESTIGATION OF LONGITUDINAL CONTROL 
CHARACTERISTICS OF A WING-TIP CONTROL 
SURFACE ON A SWEPTBACK WING AT TRANSONIC 
SPEEDS BY THE NACA WING- FLOW METHOD. 
James P. Trant, Jr. June 1952. 23p. diagrs., 
photos., tab. (NACA RM L52B15a) 

CONTROL EFFECTIVENESS AND HINGE-MOMENT 
CHARACTERISTICS AT LOW SPEED OF LARGE- 
CHORD, HORN-BALANCED, FLAP-TYPE CON- 
TROLS ON A TRIANGULAR WING OF ASPECT 
RATIO 2. Jules B. Dods, Jr. August 1952. 53p. 
diagrs., photos., 2 tabs. (NACA RM A52F13) 

THE AERODYNAMIC CHARACTERISTICS AT 
TRANSONIC SPEEDS OF AN ALL-MOVABLE, 
TAPERED, 45° SWEPTBACK, ASPECT-RATIO-4 
TAIL DEFLECTED ABOUT A SKEWED HINGE AXIS 
AND EQUIPPED WITH AN INSET UNBALANCING 
TAB. James M. Watson. September 1953. 40p. 
diagrs. (NACA RM L53H13) 

THEORETICAL INVESTIGATION OF THE EFFECTS 
UPON LIFT OF A GAP BETWEEN WING AND BODY 
OF A SLENDER WING-BODY COMBINATION. Duane 
W. Dugan and Katsumi Hikido. August 1954. 41p. 
diagrs. (NACA TN 3224) 

REYNOLDS NUMBER EFFECTS 
(1.2.2.5) 

QUALITATIVE MEASUREMENTS OF RELATIVE 
FLAP EFFECTIVENESS AT TRANSONIC SPEEDS 
ON A SERIES OF FIVE THIN AIRFOILS WITH 25- 
PERCENT -CHORD FLAPS AND VARIOUS AMOUNTS 
OF SWEEPBACK. Harold L. Crane and Milton D. 
McLauj^lin. May 17, 1948. 24p. diagrs., photos. 
(NACA RM L8A22) 

INVESTIGATION AT SUPERSONIC SPEED (M = 1. 53) 
OF THE PRESSURE DISTRIBUTION OVER A 63° 
SWEPT AIRFOIL OF BICONVEX SECTION AT 
ZERO LIFT. Charles W. Frick and John W. Boyd. 
June 10, 1948. 33p. diagrs. , photos. (NACA 
RM ABC22) 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
WITH A SWEPTBACK WING AND TAIL FROM 
TESTS AT TRANSONIC SPEEDS BY THE NACA 
WING-FLOW METHOD. Richard H. Sawyer and 
Lindsay J. Lina. July 23, 1948. 42p. diagrs., 
photos., tab. (NACA RM L8B19) 

LANDING CHARACTERISTICS OF HIGH-SPEED 
WINGS. Herbert A. Wilson, Jr. and Laurence K. 
Loftin, Jr. September 21, 1948. 21p. diagrs. 
(NACA RM L8A28e) 

INVESTIGATION AT SUPERSONIC SPEED (M =1.53) 
OF THE PRESSURE DISTRIBUTION OVER A 63° 
SWEPT AIRFOIL OF BICONVEX SECTION AT SEV- 
ERAL ANGLES OF ATTACK. John W. Boyd, EUiott 
D. Katzen and Charles W. Frick. September 24, 

1948. 41p. diagrs., photos., tab. (NACA RM A8F22) 

EFFECT OF SWEEPBACK ON THE LOW -SPEED 
STATIC AND ROLUNG STABILITY DERIVATIVES 
OF THIN TAPERED WINGS OF ASPECT RATIO 4. 
William Letko and Walter D. Wolhart. August 9, 

1949. 36p. diagrs., photo. (NACA RM L9F14) 

EFFECT OF AIRFOIL SECTION AND TIP TANKS 
ON THE AERODYNAMIC CHARACTERISTICS AT 
HIGH SUBSONIC SPEEDS OF AN UNSWEPT WING 
OF ASPECT RATIO 5. 16 AND TAPER RATIO 0.61. 
H. Norman Silvers and Kenneth P. Spreemann. 
December 1, 1949. 30p. diagrs., photos., 2 tabs. 
(NACA RM L9J04) 

THE EFFECT OF ASPECT RATIO ON THE SUB- 
SONIC AERODYNAMIC CHARACTERISTICS OF 
WINGS WITH NACA 65i-210 SECTIONS. Warren H. 
Nelson and Albert L. Erickson. February 3, 1950. 
31p. diagrs., photos., tab. (NACA RM A9K18) 

MAXIMUM -LIFT INVESTIGATION AT MACH NUM- 
BERS FROM 0.05 TO 1.20 OF A WING WITH LEAD- 
ING EDGE SWEPT BACK 42°. Thomas R. Turner. 
February 14, 1950. 21p. diagrs. (NACA 
RM L9K03) 

WING-FLOW MEASUREMENTS OF LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
A CANARD AIRPLANE CONFIGURATION WITH A 
45° SWEPTBACK WING AND A TRIANGULAR ALL- 
MOVABLE CONTROL SURFACE. Harold L. Crane 
and James J. Adams. August 25, 1950. 53p. 
diagrs., photo. (NACA RM L50A31) 

SUMMARY REPORT OF RESULTS OBTAINED DUR- 
ING DEMONSTRATION TESTS OF THE NORTHROP 
X-4 AIRPLANES. Melvin Sadoff and Thomas R. 
Sisk. December 13, 1950. 46p. diagrs., photos., 
tab. (NACA RM A50I01) 

STATIC LONGITUDINAL STABILITY AND 
DYNAMIC CHARACTERISTICS AT HIGH ANGLES 
OF ATTACK AND AT LOW REYNOLDS NUMBERS 
OF A MODEL OF THE X-3 SUPERSONIC RESEARCH 
AIRPLANE. Sanger M. Burk, Jr. and Burton E. 
Hultz. February 6, 1951. 76p. diagrs., photos., 
4 tabs. (NACA RM L50L19) 

THE EFFECTS OF MACH NUMBER AND REYNOLDS 
NUMBER ON THE AERODYNAMIC CHARACTERIS- 
TICS OF SEVERAL 12-PERCENT-THICK WINGS 
HAVING 35° OF SWEEPBACK AND VARIOUS 
AMOUNTS OF CAMBER. Bruce E. Tinling and W. 
Richard Kolk. February 23, 1951. 68p. diagrs., 
photo., tab. (NACA RM A50K27) 

WIND-TUNNEL INVESTIGATION AT HIGH AND LOW 
SUBSONIC MACH NUMBERS OF A THIN SWEPT- 
BACK WING HAVING AN AIRFOIL SECTION DE- 
SIGNED FOR HIGH MAXIMUM LIFT. Stanley F. 
Racisz and Nicholas J. Paradiso. February 1952. 
46p. diagrs., photo., tab. (NACA RM L51L04) 



AERODYNAMICS 

WINGS (1. 2) 39 



Reynolds Number Effects - 
Complete Wings (Cont. ) 

FULL-SCALE WIND"-TUNNeL INVESTIGATION Ot 
THE EFFECTS OF WING MODIFICATIONS AND 
HORIZONTAL-TAIL LOCATION ON THE LOW- 
SPEED STATIC LONGITUDINAL CHARACTERISTICS 
OF A 35° SWEPT -WING AIRPLANE. Ralph L. Makl. 
April 1952. 54p. diagrs., photos., 7 tabs. (NACA 
RM A52B05) 

INVESTIGATION OF LIFT AND CENTER OF PRES- 
SURE OF LOW -ASPECT-RATIO, CRUCIFORM, 
TRIANGULAR, AND RECTANGULAR WINGS IN 
COMBINATION WITH A SLENDER FUSELAGE AT 
HIGH SUPERSONIC SPEEDS. Thomas N. Canning 
and Billy Pat Denardo. June 1952. 28p. diagrs., 
photos. (NACA RM A52C24) 

CONTROL EFFECTIVENESS AND HDJGE-MOMENT 
CHARACTERISTICS AT LOW SPEED OF LARGE- 
CHORD, HORN-BALANCED, FLAP-TYPE CON- 
TROLS ON A TRIANGULAR WING OF ASPECT 
RATIO 2. Jules B. Dods, Jr. August 1952. 53p. 
diagrs., photos., 2 tabs. (NACA RM A52F13) 

EFFECTS OF ROUGHNESS AND REYNOLDS NUM- 
BER ON THE NONLINEAR LIFT CHARACTERISTICS 
OF A WING WITH MODIFIED HEXAGONAL AIRFOIL 
SECTIONS. Milton A. Schwartzberg. 
February 1953. 18p. diagrs., photo. (NACA 
RM L52L26a) 

MACH NUMBER EFFECTS 
(1.2. 2„ 6) 



DRAG MEASUREMENTS OF A 34° SWEPT- 
FORWARD AND SWEPT-BACK NACA 65-009 AIR- 
FOIL OF ASPECT RATIO 2.7 AS DETERMINED BY 
FLIGHT TESTS AT SUPERSONIC SPEEDS. Sidney 
R. Alexander. February 20, 1947. lip. diagrs., 
photos. (NACA RM L6I11) 

DRAG OF A WING-BODY CONFIGURATION CON- 
SISTING OF A SWEPT-FORWARD TAPERED WING 
MOUNTED ON A BODY OF FINENESS RATIO 12 
MEASURED DURING FREE FALL AT TRANSONIC 
SPEEDS. Jim Rogers Thompson and Charles W. 
Mathews. March 13, 1947. 15p. diagrs., photos. 
(NACA RM L6L24) 

LONGITUDINAL STABIUTY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
WITH A SWEPT-BACK TAIL FROM TESTS AT 
TRANSONIC SPEEDS BY THE NACA WING-FLOW 
METHOD. John A. Zalovcik and Richard H. Sawyer. 
March 28, 1947. 30p. diagrs., photos., tab. (NACA 
RM L6K21) 

DRAG MEASUREMENTS OF A SWEPT-BACK WING 
HAVING INVERSE TAPER AS DETERMINED BY 
FLIGHT TESTS AT SUPERSONIC SPEEDS. Sidney 
R. Alexander. April 8, 1947. 12p. diagrs., photo. 
(NACA RM L6L30) 

OBSERVATIONS ON AN AILERON-FLUTTER IN- 
STABILITY ENCOUNTERED ON A 45° SWEPT- 
BACK WING IN TRANSONIC AND SUPERSONIC 
FLIGHT. Marvin Pitkin, William N. Gardner and 
Howard J. Curfman, Jr. April 11, 1947. 23p. 
diagrs., photos. (NACA RM L6L09) 

FLIGHT-TEST MEASUREMENTS OF AILERON CON- 
TROL SURFACE BEHAVIOUR AT SUPERCRITICAL 
MACH NUMBERS. Harvey H. Brown, George A. 
Rathert, Jr. and Lawrence A. Clousing. April 23, 
1947. 26p. diagrs., photos., 2 tabs (NACA 
RM A7A15) 



FORCE AND LONGITUDINAL CONTROL CHARAC- 
TERISTICS OF A 1/16 - SCALE MODEL OF THE 
BELL XS-1 TRANSONIC RESEARCH AIRPLANE AT 
HIGH MACH NUMBERS. Axel T. Mattson. May 21, 

1947. 32p. diagrs., photo., tab. (NACA RM L7A03) 

MEASUREMENTS OF THE EFFECTS OF THICK- 
NESS RATIO AND ASPECT RATIO ON THE DRAG 
OF RECTANGULAR-PLAN-FORM AIRFOILS AT 
TRANSONIC SPEEDS. Jim Rogers Thompson and 
Charles W. Mathews. June 20, 1947. 17p. diagrs., 
photo. (NACA RM L7E08) 

FLIGHT TESTS TO DETERMINE THE EFFECT OF 
TAPER ON THE ZERO-LIFT DRAG OF WINGS AT 
LOW SUPERSONIC SPEEDS. Sidney R. Alexander 
and Robert L. Nelson. July 13, 1947. 19p. diagrs., 
photos. (NACA RM L7E26) 

A TORSIONAL STIFFNESS CRITERION FOR PRE- 
VENTING FLUTTER OF WINGS OF SUPERSONIC 
MISSILES. Bernard Budiansky, Joseph N. Kotanchik 
and Patrick T. Chiarito. August 28, 1947. 14p. 
diagrs., tab. (NACA RM L7G02) 

AN ANALYSIS OF LONGITUDINAL-CONTROL 
PROBLEMS ENCOUNTERED IN FLIGHT AT TRAN- 
SONIC SPEEDS WITH A JET-PROPELLED AIR- 
PLANE. Harvey H. Brown, L. Stewart Rolls and 
Lawrence A. Clousing. September 25, 1947. 56p. 
diagrs., photos., 3 tabs. (NACA RM A7G03) 

HIGH-SPEED WIND-TUNNEL TESTS OF A MODEL 
PURSUIT AIRPLANE AND CORRELATION WITH 
FLIGHT -TEST RESULTS. Joseph W. Cleary and 
Lyle J. Gray. January 21, 1948. 56p. diagrs., 
photos. (NACA RM A7I16) 

FLIGHT TESTS TO DETERMINE THE EFFECT OF 
AIRFOIL SECTION PROFILE AND THICKNESS 
RATIO ON THE ZERO-LIFT DRAG OF LOW- 
ASPECT-RATIO WINGS AT SUPERSONIC SPEEDS. 
EUls Katz. February 9, 1948. 19p. diagrs., photos. 
(NACA RM L7K14) 

FREE-FLIGHT INVESTIGATION OF THE ROLLING 
EFFECTIVENESS OF A WING-SPOILER ARRANGE- 
MENT AT HIGH SUBSONTC, TRANSONIC, AND 
SUPERSONIC SPEEDS. Carl A. SandalvL May 17, 

1948. lOp. diagrs., photo. (NACA RM L8A07) 

QUALITATIVE MEASUREMENTS OF RELATIVE 
FLAP EFFECTIVENESS AT TRANSONIC SPEEDS 
ON A SERIES OF FIVE THIN AIRFOILS WITH 25- 
PERCENT -CHORD FLAPS AND VARIOUS AMOUNTS 
OF SWEEPBACK. Harold L. Crane and Milton D. 
McLau^lin. May 17, 1948. 24p. diagrs., photos. 
(NACA RM L8A22) 

WIND-TUNNEL INVESTIGATION OF A WING- 
FUSELAGE COMBINATION WITH EXTERNAL 
STORES. H. Norman Silvers and Kenneth P. 
Spreemann. July 9, 1948. 55p. diagrs. (NACA 
RM L7K20) 

LONGITUDINAL STABILITY AND CONTROL GHAR- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
AT TRANSONIC SPEEDS AS OBTAINED BY THE 
TRANSONIC -BUMP METHOD. Joseph Weil and 
M. Leroy Spearman. July 19, 1948. 23p. diagrs., 
tab. (NACA RM L8B03) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
WITH A SWEPTBACK WING AND TAIL FROM 
TESTS AT TRANSONIC SPEEDS BY THE NACA 
WING-FLOW METHOD. Richard H. Sawyer and 
Lindsay J. Lina. July 23, 1948. 42p. diagrs., 
photos., tab. (NACA RM L8B19) 

APPLICATION OF ONE PART OF VON KARMAN'S 
TWO-DIMENSIONAL TRANSONIC SIMILARITY LAW 
TO DRAG DATA OF NACA 65-SERIES WINGS. 
Kenneth B. Amer. August 24, 1948. 9p. diagrs. 
(NACA RM L8F24) 



40 



AERODYNAMICS 
WINGS (1.2) 



Mach Number Effects - Complete 
Wings (Cont. ) 

EFFECT OF DOWNWASH ON THE ESTIMATED 
ELEVATOR DEFLECTION REQUIRED FOR TRIM 
OF THE XS-1 AIRPLANE AT SUPERSONIC SPEEDS. 
Tames T. Matthews, Jr. November 1, 1948. lip. 
dlagrs. (NACA RM L8H06a) 

LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A SEMISPAN MODEL OF A 
SUPERSONIC AIRPLANE CONFIGURATION AT 
TRANSONIC SPEEDS FROM TESTS BY THE NACA 
WING-FLOW METHOD. Norman S. Silsby and 
James M. McKay. November 8, 1948. 30p. 
diagrs., photos., tab. (NACA RM L8G30) 

AERODYNAMIC CHARACTERISTICS AT SUBSONIC 
AND SUPERSONIC MACH NUMBERS OF A THIN 
TRIANGULAR WING OF ASPECT RATIO 2. I - 
MAXIMUM THICKNESS AT 20 PERCENT OF THE 
CHORD. Robert E. Berggren and James L. 
Simimers. November 19, 1948. 41p. dlagrs., photos. 
(NACA RM A8I16) 

ADDITIONAL FREE-FLIGHT TESTS OF THE ROLL- 
ING EFFECTIVENESS OF SEVERAL WING-SPOILER 
ARRANGEMENTS AT HIGH SUBSONIC, TRANSONIC, 
AND SUPERSONIC SPEEDS. H. Kurt Strass. 
November 24, 1948. 16p. diagrs., photos. .(NACA 
RM L8I23) 

AERODYNAMIC CHARACTERISTICS AT SUBSONIC 
AND SUPERSONIC MACH NUMBERS OF A THIN 
TRLANGULAR WING OF ASPECT RATIO 2. II - 
MAXIMUM THICKNESS AT MIDCHORD. Harold J. 
Walker and Robert E. Berggren. December 3, 1948. 
41p. diagrs., photos. (NACA RM A8I20) 

AN INVESTIGATION OF AILERON OSCILLATIONS 
AT TRANSONIC SPEEDS ON NACA 23012 AND 
NACA 65-212 AIRFOILS BY THE WING-FLOW 
METHOD. Harold L. Crane. December 29, 1948. 
9p. diagrs., photo. (NACA RM L8K29) 

AERODYNAMIC CHARACTERKTICS AT SUBSONIC 
AND TRANSONIC SPEEDS OF A 42.7° SWEPTBACK 
WING MODEL HAVING AN AILERON WITH FINITE 
TRAILING-EDGE THICKNESS. Thomas R. Turner, 
Vernard E. Lockwood and Raymond D. Vogler. 
January 12, 1949. 24p. dlagrs., photo. (NACA 
RM L8K02) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Joseph Weil and Kenneth W. Goodson. 
February 24, 1949. 28p. diagrs., photo., tab. 
(NACA RM L9A21) 

MEASUREMENTS OF AERODYNAMIC CHARACTER- 
ISTICS OF A 35° SWEPTBACK NACA 65-009 AIR- 
FOIL MODEL WITH 1/4-CHORD HORN-BALANCED 
FLAP BY THE NACA WING-FLOW METHOD. 
Harold I. Johnson and B. Porter Brown. April 18, 
1949. 59p. diagrs., photo. (NACA RM L9B23a) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 35°, 
ASPECT RATIO 4, TAPER RATIO 0. 6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. William C. Sleeman, Jr. and Robert E. 
Becht. April 21, 1949. 29p. diagrs., photo., tab. 
(NACA RM L9B25) 

HIGH-SUBSONIC DAMPING-IN-ROLL CHARACTER. 
ISTICS OF A WING WITH THE QUARTER-CHORD 
LINE SWEPT BACK 35° AND WITH ASPECT RATIO 
3 AND TAPER RATIO 0.6. Boyd C. Myers, n and 
Richard E. Kuhn. May 10, 1949. 21p. diagrs., 
photo., tab. (NACA RM L9C23) 



INVESTIGATIONS AT SUPERSONIC SPEEDS OF 22 
TRIANGULAR WINGS REPRESENTING TWO AIR- 
FOIL SECTIONS FOR EACH OF 11 APEX ANGLES. 
Eugene S. Love. May 10, 1949. lOOp. diagrs., 
photos., 3 tabs. (NACA RM L9D07) 

WIND-TUNNEL INVESTIGATION AT HICHI SUB- 
SONIC SPEEDS OF THE LATERAL -CONTROL 
CHARACTERISTICS OF AN AILERON AND A 
STEPPED SPOILER ON A WING WITH LEADING 
EDGE SWEPT BACK 51. 3°. LesUe E. Schneiter 
and John R. Hagerman. June 7, 1949. 34p. diagrs., 
photo. (NACA RM L9D06) 

EFFECTS OF MACH NUMBER AND SWEEP ON THE 
DAMPING-IN-ROLL CHARACTERISTICS OF WINGS 
OF ASPECT RATIO 4. Richard E. Kuhn and Boyd 

C. Myers, II. June 27, 1949. 28p. diagrs., photo. 
(NACA RM L9E10) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 4, TAPER RATIO 0.3, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC-BUMP 
METHOD. Boyd C. Myers, II and Thomas J. King, 
Jr. July 20, 1949. 28p. diagrs., photo., tab. 
(NACA RM L9E25) 

DAMPING-IN-ROLL CHARACTERISTICS OF A 
42. 7° SWEPT -BACK WING AS DETERMINED FROM 
A WIND-TUNNEL INVESTIGATION OF A TWISTED 
SEMISPAN WING. Vernard E. Lockwood. August 8, 
1949. 23p. diagrs. (NACA RM L9F15) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER - 
CHORD LINE SWEPT BACK 45°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. Raymond 

D. Vogler. August 15, 1949. 22p. diagrs. (NACA 
RM L9F29a) 

TESTS OF LIFTING SURFACES ON CONICAL AND 
CYLINDRICAL PORTIONS OF A BODY AT SUBSONIC 
MACH NUMBERS ANDiAT A MACH NUMBER OF 1.2. 
Robert S. Osborne and John B. Wright. September 2, 
1949. 22p. diagrs. (NACA RM L9F29) 

AERODYNAMIC CHARACTERBTICS OF A DELTA 
WING WITH LEADING EDGE SWEPT BACK 45°, 
ASPECT RATIO 4, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. William 
C. Sleeman, Jr. and Robert E. Becht. September 6, 
1949. 29p. diagrs., photo., tab. (NACA 
RM L9G22a) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 60°, 
ASPECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Thomas J. King, Jr. and Boyd C. Myers, 
II. September 6, 1949. 32p. diagrs., photos., tab. 
(NACA RM L9G27) 

AERODYNAMIC CHARACTERSTICS OF A WING 
WITH UNSWEPT QUARTER -CHORD LINE, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A006 
AIRFOIL SECTION. TRANSONIC -BUMP METHOD. 
Kenneth W. Goodson and William D. Morrison, Jr. 
October 21, 1949. 32p. diagrs., photos^, tab. 
(NACA RM L9H22) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMF 
METHOD. Kenneth W. Goodson and Albert G. Few, 
Jr. November 1, 1949. 34p. diagrs., photos., tab. 
(NACA RM L9I08) 



AERODYNAMICS 
WINGS (1.2) 



41 



Mach Number Effects - Complete 
Wings (Cont. ) 

WIND-TUNNEL INVESTIGATION AT LOW TRAN- 
SONIC SPEEDS OF THE EFFECTS OF NUMBER OF 
WINGS ON THE LATERAL-CONTROL EFFECTIVE- 
NESS OF AN RM-5 TEST VEHICLE. Harold S. 
Johnson. November 29, 1949, 15p. diagrs., photo., 
tab. (NACA RM L9H16) 

EFFECT OF AIRFOIL SECTION AND TIP TANKS 
ON THE AERODYNAMIC CHARACTERISTICS AT 
HIGH SUBSONIC SPEEDS OF AN UNSWEPT WING 
OF ASPECT RATIO 5. 16 AND TAPER RATIO 0.61. 
H. Norman Silvers and Kenneth P. Spreemann. 
December 1, 1949. 30p. diagrs., photos., 2 tabs. 
(NACA RM L9J04) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 35°, 
ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. William C. Sleeman, Jr. and William D. 
Morrison, Jr. December 12, 1949. 32p. diagrs., 
photos., tab. (NACA RM L9K10a) 

A FREE-FLIGHT TECHNIQUE FOR MEASURING 
DAMPING IN ROLL BY USE OF ROCKET-POWERED 
MODELS AND SOME INITIAL RESULTS FOR 
RECTANGULAR WINGS. James L. Edmondson and 
E. Claude Sanders, Jr. December 20, 1949. 25p. 
diagrs., photos. (NACA RM L9I01) 

MEASUREMENTS OF AERODYNAMIC CHARACTER- 
ISTICS OF A 35° SWEPTBACK NACA 65-009 AIR- 
FOIL MODEL WITH 1/4-CHORD BEVELLED- 
TRAILING-EDGE FLAP AND TRIM TAB BY THE 
NACA WING-FLOW METHOD. Harold I. Johnson 
and B. Porter Brown. January 6, 1950. 68p. 
diagrs., photo. (NACA RM L9K11) 

THE EFFECT OF TIP TANKS ON THE ROLLING 
CHARACTERISTICS AT HIGH SUBSONIC MACH 
NUMBERS OF A WING HAVING AN ASPECT RATIO 
OF 3 WITH QUARTER-CHORD LINE SWEPT BACK 
35°. Richard E. Kuhn and Boyd C. Myers, H. 
January 17, 1950. 27^). diagrs., photo., 2 tabs. 
(NACA RM L9J19) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER- 
CHORD LINE SWEPT BACK 35°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. Robert F. 
Thompson. January 25, 1950. 22p. diagrs., tab. 
(NACA RM L9L12a) 

WIND-TUNNEL INVESTIGATION AT MACH NUM- 
BERS FROM 0.50 TO 1.20 OF AN ALL-MOVABLE 
TRIANGULAR WING OF ASPECT RATtO 4 ALONE 
AND WITH A BODY. Louis S. Stivers, Jr. and 
Alexander W. Malick. February 2, 1950. 45p. 
diagrs., photos., tab. (NACA RM A9L01) 

THE EFFECT OF ASPECT RATIO ON THE SUB- 
SONIC AERODYNAMIC CHARACTERISTICS OF 
WINGS WITH NACA 65i-210 SECTIONS. Warren H. 
Nelson and Albert L. Erickson. February 3, 1950. 
31p. diagrs., photos., tab. (NACA RM A9K18) 

MAXllMUM-LIFT INVESTIGATION AT MACH NUM- 
BERS FROM 0.05 TO 1.20 OF A WING WITH LEAD- 
ING EDGE SWEPT BACK 42°. Thomas R. Turner. 
Febrvary 14, 1950. 21p. diagrs. (NACA 
RM L9K03) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 60°, 
ASPECT RATIO 2, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC-BUMP 
METHOD. Boyd C. Myers, H and Thomas J. King, 
Jr. February 24, 1950. 31p. diagrs., photos., tab. 
(NACA RM L50A12) 



LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER- 
CHORD LINE SWEPT BACK 60°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC-BUMP METHOD. Raymond 
D. Vogler. March 2, 1950. 21p. diagrs. (NACA 
RM L50A17) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH UNSWEPT QUARTER-CHORD LINE, ASPECT 
RATIO 2, TAPER RATIO 0.78, AND NACA 65A004 
AIRFOIL SECTION. TRANSONIC -BUMP METHOD. 
Edward C. Polhamus and George S. Campbell. 
March 8, 1950. 17p. diagrs., photos., tab. (NACA 
RM L50A18) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH UNSWEPT 
QUARTER-CHORD LINE, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC-BUMP METHOD. 
Alexander D. Hammond. March 10, 1950. 20p. 
diagrs. (NACA RM L50A03) 

THE DAMPING IN ROLL OF ROCKET-POWERED 
TEST VEHICLES HAVING RECTANGULAR WINGS 
WITH NACA 65-006 AND SYMMETRICAL DOUBLE- 
WEDGE AIRFOIL SECTIONS OF ASPECT RATIO 4.5. 
Albert E. Dietz and James L. Edmondson. March 29, 
1950. 12p. diagrs. (NACA RM L50B10) 

INVESTIGATION AT HIGH SUBSONIC SPEEDS OF A 
45° SWEPTBACK HORIZONTAL TAIL WITH PLAIN 
AND HORN-BALANCED CONTROL SURFACES. 
Harold S. Johnson and Robert F. Thompson. 
March 31, 1950. 44p. diagrs., photo., tab. (NACA 
RM L50B13) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 
65A009 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Kenneth P. Spreemann, William D. 
Morrison, Jr. and Thomas B. Pasteur, Jr. April 6, 
1950. 33p. diagrs., photos., tab. (NACA 
RM L50B03a) 

MAXIMUM-LIFT INVESTIGATION OF A 1/40-SCALE 
X-1 AIRPLANE WING AT MACH NUMBERS FROM 
0.60 TO 1.15. Thomas R. Turner. April 21, 1950. 
18p. diagrs. (NACA RM L50C28) 

FLIGHT INVESTIGATION OF THE EFFECT OF 
THICKENING THE AILERON TRAILING EDGE ON 
CONTROL EFFECTIVENESS FOR SWEPTBACK 
TAPERED WINGS HAVING SHARP- AND ROUND- 
NOSE SECTIONS. H. Kurt Strass and Edison M. 
Fields. May 2, 1950. 20p. diagrs., photo., tab. 
(NACA RM L9L19) 

AERODYNAMIC CHARACTERISTICS WITH FIXED 
AND FREE TRANSITION OF A MODIFIED DELTA 
WING IN COMBINATION WITH A FUSELAGE AT 
HIGH SUBSONIC SPEEIffi. Edward C. Polhamus and 
Thomas J. King, Jr. May 2, 1950. 19p. diagrs., 
photos. (NACA RM L50C21) 

AERODYNAMIC AND LATERAL-CONTROL CHAR- 
ACTERISTICS OF A 1/28-SCALE MODEL OF THE 
BELL X-1 AIRPLANE WING-FUSELAGE COMBINA- 
TION. TRANSONIC -BUMP METHOD. Vernard E. 
Lockwood. May 5, 1950. 28p. diagrs., tab. (NACA 
RM L50C22) 

AERODYNAMIC CHARACTERISTKS AT A MACH 
NUMBER OF 1.25 OF A 6 -PERCENT-THICK TRIAN- 
GULAR WING AND 6- AND 9-PERCENT-THICK TRI- 
ANGULAR WINGS IN COMBINATION WITH A FUSE- 
LAGE. WING ASPECT RATIO 2.31, BICONVEX AIR- 
FOIL SECTIONS. Albert W. Hall and Garland J. 
Morris. May 5, 1950. 22p. diagrs., photo., 2 tabs. 
(NACA RM L50D05) 



42 



AERODYNAMICS 
WINGS (1.2) 



Mach Number Effects - Complete 
Wings (Cont. ) 

AERODYNAMIC CHARACTERISTICS OF A V/Ui<J 
WITH UNSWEPT QUARTER-CHORD LINE, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A004 
AIRFOIL SECTION. TRANSONIC -BUMP METHOD. 
Boyd C. Myers, n and James W. Wiggins. May 8, 
1950. 31p. diagrs., photos., tab. (NACA 
RM L50C16) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE AND SPOILER-TYPE CONTROLS ON A WING 
WITH QUARTER -CHORD-LINE SWEEPBACK OF 
6,0°, ASPECT RATIO 2, TAPER RATIO 0.6, AND* 
NACA 65A006 AIRFOIL SECTION. TRANSONIC- 
BUMP METHOD. Alexander D. Hammond. July 18, 
1950. 26p. diagrs. (NACA RM L50E09) 

INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
METHOIffi OF ALLEVIATING THE ADVERSE 
INTERFERENCE AT THE ROOT OF A SWEPT- 
BACKWING. LeeE. Boddy. August 10, 1950. 31p. 
diagrs., photos. (NACA RM A50E26) 

FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.6 to 1.7 TO DETERMINE DRAG AND BASE 
PRESSURES ON A BLUNT -TRAILING-EDGE AIR- 
FOIL AND DRAG OF DIAMOND AND CIRCULAR- 
ARC AIRFOILS AT ZERO LIFT. John D. Morrow 
and Ellis Katz. August 11, 1950. 25p. diagrs., 
photos. (NACA RM L50E19a) 

MEASUREMENTS OF THE EFFECT OF TRAILING- 
EDGE THICKNESS ON THE ZERO-LIFT DRAG OF 
THIN LOW-ASPECT-RATIO WINGS. John D. 
Morrow. August 14, 19^0. 12p. diagrs., photo. 
(NACA RM L50F26) 

INVESTIGATION OF FLAP-TYPE AILERONS ON AN 
UNTAPERED WING HAVING AN ASPECT RATIO OF 
3.7, 45° SWEEPBACK, AND AN NACA 65A009 AIR- 
FOIL SECTION. TRANSONIC -BUMP METHOD. 
Richard G. MacLeod. August 23, 1950. 18p. 
diagrs. (NACA RM L50G03) 

DAMPING IN ROLL OF RECTANGULAR WINGS OF 
SEVERAL ASPECT RATIOS AND NACA 65A-SERIES 
AIRFOIL SECTIONS OF SEVERAL THICKNESS 
RATIOS AT TRANSONIC AND SUPERSONIC SPEEDS 
AS DETERMINED WITH ROCKET-POWERED 
MODEi£. James L. Edmondson. August 24, 1950. 
16p. diagrs. (NACA RM L50E26) 

WING-FLOW MEASUREMENTS OF LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
A CANARD AIRPLANE CONFIGURATION WITH A 
45° SWEPTBACK WING AND A TRIANGULAR ALL- 
MOVABLE CONTROL SURFACE. Harold L. Crane 
and James J. Adams. August 25, 1950. 53p. 
diagrs., photo. (NACA RM L50A3 1) 

FLIGHT TESTS AT SUPERSONIC SPEEDS TO 
DETERMINE THE EFFECT OF TAPER ON THE 
ZERO-LIFT DRAG OF SWEPTBACK LOW-ASPECT- 
RATIO WINGS. Murray Pittel. September 5, 1950. 
23p. diagrs., photos. (NACA RM L50F30a) 

INVESTIGATION AT TRANSONIC SPEEDS OF A 
35-PERCENT-CHORD AILERON ON A TAPERED 
WEDGE-TYPE WING OF ASPECT RATIO 2.5 WITH 
AND WITHOUT A FUSELAGE. Thomas R. Turner 
and Joseph E. Fikes. September 8, 1950. 25p. 
diagrs. (NACA RM L50G13a) 

PRELIMINARY FLIGHT INVESTIGATION OF THE 
WING-DROPPING TENDENCY AND LATERAL- 
CONTRtDL CHARACTERISTICS OF A 35° SWEPT- 
WING AIRPLANE AT TRANSONIC MACH NUMBERS. 
George A. Rathert, Jr. , L. Stewart Rolls, Lee 
Winograd and George E. Cooper. September 11, 
1950. 14p. diagrs., photo., tab. (NACA RM A50H03) 



MEASUREMENTS OF AERODYNAMIC CHARACTER- 
ISTICS OF A 35° SWEPTBACK NACA 65-009 AIR- 
FOIL MODEt WITH 1/4-CHORD FLAP HAVING A 
31-PERCENT-FLAP-CHORD OVERHANG BALANCE 
BY THE NACA WING-FLOW METHOD. Harold 1. 
Johnson and Harold R. Goodman. September 25, 
1950. 38p. diagrs., photo. (NACA RM L50H09) 
EFFECTS OF SWEEP ON THE MAXIMUM -LIFT 
CHARACTERBTICS OF FOUR ASPECT-RATIO-4 
WINGS AT TRANSONIC SPEEDS. Thomas R. Turner. 
October 3, 1950. 25p. diagrs. (NACA RM L50H11) 

PRELIMINARY FUGHT INVESTIGATION OF THE 
DYNAMIC LONGITUDINAL-STABIUTY CHARAC- 
TERISTICS OF A 35° SWEPT-WDJG AIRPLANE. 
William C. Triplett and Rudolph D. Van Dyke, Jr. 
December 11, 1950. 26p. diagrs., photo., tab. 
(NACA RM A50J09a) 

INVESTIGATION OF THE DOWNWASH AND WAKE 
BEHIND A TRIANGULAR WING OF ASPECT RATIO 
4 AT SUBSONIC AND SUPERSONIC MACH NUM- 
BERS. Harold J. Walker and Louis S. Stivers, Jr. 
December 12, 1950. 32p. diagrs. (NACA 
RM A50I14a) 

SUMMARY REPORT OF RESULTS OBTAINED DUR- 
ING DEMONSTRATION TESTS OF THE NORTHROP 
X-4 AIRPLANES. Melvin Sadoft and Thomas R. 
Sisk. December 13, 1950. 46p. diagrs., photos., 
tab. (NACA RM A50I01) 

WIND-TUNNEL INVESTIGATION AT MACH 
NUMBERS FROM 0.50 TO 1.29 OF AN UNSWEPT 
TAPERED WING OF ASPECT RATIO 2.67 WITH 
LEADING- AND TRAILING-EDGE FLAPS - 
TRAILING-EDGE FLAPS DEFLECTED. Louis S. 
Stivers, Jr. and Alexander W. Malick. 
December 13, 1950. 45p. diagrs., photo., 5 tabs. 
(NACA RM A50J09b) 

EFFECTS OF SWEEP ON THE DAMPING-IN-ROLL 
CHARACTERISTICS OF THREE SWEPTBACK 
WINGS HAVING AN ASPECT RATIO OF 4 AT 
TRANSONIC SPEEDS. Vernard E. Lockwood. 
December 14, 1950. 23p. diagrs. (NACA 
RM L50J19) 

TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED IN 
FLIGHT ON THE WING OF THE DOUGLAS D-558-I 
AIRPLANE FOR A 1 g STALL, A SPEED RUN TO A 
I^ACH NUMBER OF 0.90, AND A WIND-UP TTON 
AT A MACH NUMBER OF 0.86. Earl R. Keener and 
Mary Pierce. December 15, 1950. 40p. diagrs., 
photos., 5 tabs. (NACA RM L50J10) 

EFFECT OF AN END PLATE ON THE AERODY- 
NAMIC CHARACTERISTICS OF A 20.55° SWEPT- 
BACK WING WITH AN ASPECT RATIO OF 2.67 AND 
A TAPER RATIO OF 0.5. TRANSONIC -BUMP 
METHOD. James M. Watson. December 21, 1950. 
15p. diagrs., photo. (NACA RM L50H28a) 

INVESTIGATION OF A 42.7° SWEPTBACK WING 
MODEL TO DETERMINE THE EFFECTS OF 
TRAILING-EDGE THICKNESS ON THE AILERON 
HINGE -MOMENT AND FLUTTER CHARACTER- 
ISTICS AT TRANSONIC SPEEDS. Robert F. 
Thompson. December 26, 1950. 42p. diagrs., 
photos., 2 tabs. (NACA RM L50J06) 

TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED 
IN FLIGHT ON THE WING OF THE DOUGLAS 
D-558-I AIRPLANE THROUGHOUT THE NORMAL- 
FORCE-COEFFICIENT RANGE AT MACH NUMBERS 
OF 0.67, 0.74, 0.78, AND 0.82. Earl R. Keener, 
James R. Peele and Julia B. Woodbridge. 
January 29, 1951. 37p. diagrs., photos., 6 tabs. 
(NACA RM L50L12a) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 60° DELTA WING EQUIPPED WITH A 
TRIANGULAR PLAN-FORM CONTROL HAVING A 
SKEWED HINGE AXIS AND AN OVERHANG BAL- 
ANCE. TRANSONIC-BUMP METHOD.' Harleth G. 
Wiley. February 6, 1951. 31p. diagrs. (NACA 
RM L50L01) 



AERODYNAMICS 
WINGS (1.2) 



43 



Mach Number Effects - Complete 
Wings (Cont. ) 

THK EFFECTS OF MACH NUMBER AND REYNOLDS 
NUMBER ON THE AERODYNAMIC CHARACTERIS- 
TICS OF SEVERAL 12-PERCENT -THICK WINGS 
HAVING 350 OF SWEEPBACK AND VARIOUS 
AMOUNTS OF CAMBER. Bruce E. Tinling and W. 
Richard Kolk. February 23, 1951. 68p. diagrs., 
photo., tab. (NACA RM A50K27) 

WIND-TUNNEL INVESTIGATION AT MACH NUM- 
BERS FROM 0.50 TO 1.29 OF AN UNSWEPT, 
TAPERED WDJG OF ASPECT RATIO 2.67 WITH 
LEADING- AND TRAIUNG-EDGE FLAPS - 
LEADING-EDGE FLAPS DEFLECTED. Louis S. 
Stivers, Jr. and Alexander W. Malick. February 26, 
1951. 37p. diagrs., photo., 5 tabs. (NACA 
RM A50K10) 

EXPERIMENTAL DOWNWASH AND WAKE CHAR- 
ACTERISTICS AT SUBSONIC AND SUPERSONIC 
MACH NUMBERS BEHIND AN UNSWEPT, TAPERED 
WING OF ASPECT RATIO 2.67 WITH LEADING- 
AND TRAELING-EDGE FLAPS. Harold J. Walker, 
Louis S. Stivers, Jr. and Luther Beard, Jr. 
April 20, 1951. 43p. diagrs. (NACA RM A51B16) 

FUGHT MEASUREMENTS OF THE WING- 
DROPPING TENDENCY OF A STRAIGHT -WING JET 
AIRPLANE AT HIGH SUBSONIC MACH NUMBERS. 
Seth B. Anderson, Edward A. Ernst and Rudolph D. 
Van Dyke, Jr. April 24, 1951. 16p. diagrs., photo., 
tab. (NACA RM A51B28) 

THE TRANSONIC CHARACTERISTICS OF 17 
RECTANGULAR, SYMMETRICAL WING MODELS 
OF VARYING ASPECT RATIO AND THICKNESS. 
Warren H. Nelson and John B. McDevitt. May 10, 
1951. 91p. diagrs., photos. (NACA RM A51A12) 

PRESSURE -DISTRIBUTION MEASUREMENTS OVER 
A 45° SWEPTBACK WING AT TRANSONIC SPEEDS 
BY THE NACA WING-FLOW METHOD. Edward 

C. B. Danforth and Thomas C. O'Bryan. June 1951. 
42p. diagrs., photos. (NACA RM L51D24) 

AERODYNAMIC CHARACTERISTICS OF TAPERED 
WINGS HAVING ASPECT RATIOS OF 4, 6, AND 8, 
QUARTER-CHORD LINES SWEPT BACK 45°, AND 
NACA 631A012 AIRFOIL SECTIONS. TRANSONIC- 
BUMP METHOD. Edward C. Polhamus and 
Thomas J. King, Jr. June 13, 1951. 23p. diagrs., 
photos., 2 tabs. (NACA RM L51C26) 

AN EXPERIMENTAL STUDY AT MODERATE AND 
HIGH SUBSONIC SPEEDS OF THE FLOW OVER 
WINGS WITH 30° AND 45° OF SWEEPBACK IN 
CONJUNCTION WITH A FUSELAGE. Richard T. 
Whitcomb. June 15, 1951. 56p. diagrs., photos. 
(NACA RM L50K27) * 

AN EXPERIMENTAL STUDY OF MODERATE AND 
HIGH SUBSONIC SPEEDS OF THE FLOW OVER 
WINGS WITH 30° AND 45° OF SWEEPFORWARD • 
IN CONJUNCTION WITH A FUSELAGE. Richard T. 
Whitcomb. June 15, 1951. 47p. diagrs., photo. 
(NACA RM L50K28) 

AN EXPERIMENTAL STUDY OF MODERATE AND 
HIGH SUBSONIC SPEEDS OF THE FLOW OVER AN 
UNSWEPT WING IN CONJUNCTION WITH A FUSE- 
LAGE. Richard T. Whitcomb. June 18, 1951. 35p. 
diagrs., photos. (NACA RM L50L07) 

EFFECTS OF SPANWISE THICKNESS VARIATION 
ON THE AERODYNAMIC CHARACTERISTICS OF 
35° AND 45° SWEPTBACK WINGS OF ASPECT 
RATIO 6. TRANSONIC-BUMP METHOD. WUliam 

D. Morrison, Jr. and Paul G. Fournier. July 1951. 
38p. diagrs., photo. (NACA RM L51D19) 



CONTRIBUTIONS OF WING, TAIL, AND FUSELAGE 
TO THE AERODYNAMIC CHARACTERISTICS OF A 
SEMISPAN MODEL OF A SUPERSONIC AIRPLANE 
CONFIGURATION AT TRANSONIC SPEEDS FROM 
TESTS BY THE NACA WING-FLOW METHOD. 
Norman S. Silsby and James M. McKay. July 1951. 
34p. diagrs., photos., tab. (NACA RM L51E01) 

INVESTIGATION OF A TRIANGULAR WING IN CON- 
JUNCTION WITH A FUSELAGE AND HORIZONTAL 
TAIL TO DETERMINE DOWNWASH AND LONGITU- 
DINAL STABILITY CHARACTERISTICS - TRAN- 
SONIC BUMP METHOD. Edwin C. Allen. August 
1951. 22p. diagrs., photos. (tJACA RM A51F12a) 

COMPARISON OF AIRFOIL SECTIONS ON TWO 
TRIANGULAR-WING-FUSELAGE CONFIGURATIONS 
AT TRANSONIC SPEEDS FROM TESTS BY THE 
NACA WING-FLOW METHOD. Albert W. Hall and 
Ja.a\pa M. McKay. August 1951. 23p. diagrs., 
photo., tab. (NACA RM L51F01) 

AERODYNAMIC CHARACTERISTICS AT TRAN- 
SONIC SPEEDS OF A TAPERED 45° SWEPTBACK 
WING OF ASPECT RATIO 3 HAVING A FULL-SPAN 
FLAP-TYPE CONTROL. TRANSONIC -BUMP 
METHOD. Vernard E. Lockwood and Joseph E. 
Fikes. August 1951. 35p. diagrs. (NACA 
RM L51F06a) 

SMALL-SCALE INVESTIGATION AT TRANSONIC 
SPEEDS OF THE EFFECTS OF THICKENING THE 
INBOARD SECTION OF \ 45° SWEPTBACK WING 
OF ASPECT RATIO 4, TAPER RATIO 0.3, AND 
NACA 65A006 AIRFOIL SECTION. Kenneth P. 
Spreemann and WilUam J. Alford, Jr. August 1951. 
21p. diagrs., photo. (NACA RM L51F08a) 

TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED IN 
FLIGHT ON THE WING OF THE D-558-I RESEARCH 
AIRPLANE.THROUGH A MACH NUMBER RANGE 
OF 0.80 TO 0.89 AND THROUGHOUT THE 
NORMAL-FORCE-COEFFICIENT RANGE AT MACH 
NUMBERS OF 0.61, 0.70, 0.855, AND 0.88. Earl 
R. Keener and Rozalia M. Bandish. August 1951. 
43p. diagrs., photos., 7 tabs. (NACA RM L51F12) 

FLIGHT DETERMINATION OF THE EFFECTS OF 
WING VORTEX GENERATORS ON THE AERO- 
DYNAMIC CHARACTERISTICS OF THE DOUGLAS 
D-558-I AIRPLANE. De E. Beeler, Donald R. 
Bellman and John H. Griffith. August 14, 1951. 23p. 
diagrs., photos, tab. (NACA RM L51A23) 

A METHOD FOR THE DESIGN OF SWEPTBACK 
WINGS WARPED TO PRODUCE SPECIFIED FLIGHT 
CHARACTERISTICS AT SUPERSONIC SPEEDS. 
Warren A. Tucker. September 1951. 52p. diagrs., 
2 tabs. (NACA RM L51F08) 

EFFECTS OF SPANWISE THICKNESS VARIATION 
ON THE TRANSONIC AERODYNAMIC CHARACTER- 
ISTICS OF WINGS HAVING 35° OF SWEEPBACK, 
ASPECT RATIO 4, AND TAPER RATIO 0.60. 
William D. Morrison, Jr. and Paul G. Fournier. 
September 1951. 21p. diagrs., photo. (NACA 
RM L51F28) 

AN INVESTIGATION AT TRANSONIC SPEEDS OF 
THE EFFECTS OF CONTROL CHORD AND SPAN 
ON THE CONTROL CHARACTERISTICS OF A 
TAPERED WEDGE -TYPE WING OF ASPECT RATIO 
2.5. TRANSONIC-BUMP METHOD. Raymond D. 
Vogler, Vernard E. Lockwood and Thomas R. 
Turner. September 1951. 36p. diagrs. (NACA 
RM L51G03) 

A CORRELATION OF EXPERIMENTAL ZERO-LIFT 
DRAG OF RECTANGULAR WINGS WITH SYMMET- 
RICAL NACA 65 -SERIES AIRFOIL SECTIONS BY 
MEANS OF THE TRANSONIC SIMILARITY LAW 
FOR WINGS OF FINITE ASPECT RATIO. Edward 
C. B. Danforth. September 1951. 20p. diagrs. 
(NACA RM L51G20) 



AERODYNAMICS 
4^ WINGS (1.2) 



Mach Number Effects - Complete 
Wings (Cont. ) 

THE EFFECTS ON THE AERODYNAMIC CHARAC- 
TERISTICS OF REVERSING THE WING OF A TRI- 
ANGULAR WING-BODY COMBINATION AT TRAN- 
SONIC SPEEDS AS DETERMINED BY THE NACA 
WING- FLOW METHOD. James M. McKay and 
Albert W. Hall. October 1951. 22p. diagrs., photo., 
2 tabs. (NACA RM L51H23) 

LOAD DISTRIBUTION OVER A FUSELAGE IN COM- 
BINATION WITH A SWEPT WING AT SMALL 
ANGLES OF ATTACK AND TRANSONIC SPEEDS. 
Maurice D. White and Bonne C. Look. November 
1951. 26p. diagrs., photo., tab. (NACA RM 
A51H15) 

A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT -WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
Seth B. Anderson and Richard S. Bray. November 
1951. 33p. diagrs., photo., tab. (NACA RM A51I12) 

INVESTIGATION OF WING-TIP AILERONS ON A 
51.3° SWEPTBACK WING AT TRANSONIC SPEEDS 
BY THE TRANSONIC -BUMP METHOD. WilUam C. 
Moseley, Jr. and James M. Watson. November 1951. 
60p. diagrs. (NACA RM L5 1H27) 

SUMMARY OF RESULTS OBTAINED BY 
TRANSONIC-BUMP METHOD ON EFFECTS OF 
PLAN" FORM AND THICKNESS OF LIFT AND DRAG 
CHARACTERISTICS OF WINGS AT TRANSONIC 
SPEEDS. Edward C. Polhamus. November 1951. 
33p. diagrs., tab. (NACA RM L51H30) 

AERODYNAMIC CHARACTERISTICS OF A 
LEADING-EDGE SLAT ON A 35° SWEPT -BACK 
WING FOR MACH NUMBERS FROM 0.30 TO 0.88. 
John A. Kelly and Nora-Lee F. Hayter. December 
1951. 49p. diagrs., tab. (NACA RM A51H23) 

THE EFFECTS AT TRANSONIC SPEEDS OF THICK- 
ENING THE TRAILING EDGE OF A WING WITH A 
4-PERCENT -THICK CIRCULAR-ARC AIRFOIL. 
Joseph W. Cleary and George L. Stevens. December 
1951. 43p. diagrs., photo. (NACA RM A51J11) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A WING HAAHNG 45° SWEEP, ASPECT 
RATIO 8, TAPER RATIO 0.45, AND AIRFOIL 
SECTIONS VARYING FROM THE NACA 63A010 
SECTION AT THE ROOT TO THE NACA 63A006 
SECTION AT THE TIP. William D. Morrison, Jr. 
and Paul G. Fournier. January 1952. 22p. diagrs., 
photo. (NACA RM L51H28) 

SMALL-SCALE INVESTIGATION OF THE EFFECTS 
OF TWIST AND CAMBER ON THE AERODYNAMIC 
CHARACTERISTICS OF A 60° 42' SWEPTBACK 
WING OF ASPECT RATIO 1.94. Kenneth P. 
Spreemann and William J. Alford, Jr. January 1952. 
19p. diagrs., photo., tab. (NACA RM L51I21) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A TAPERED 45° SWEPTBACK WING 
OF ASPECT RATIO 3 HAVING A FULL-SPAN FLAP 
TYPE OF CONTROL WITH OVERHANG BALANCE. 
TRANSONIC-BUMP METHOD. Vernard E. 
Lockwood and John R. Hagerman. January 1952. 
24p. diagrs. (NACA RM L51L11) 

THE EFFECTIVENESS OF WDJG VORTEX GENER- 
ATORS IN IMPROVING THE MANEUVERING CHAR- 
ACTERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, George 
A. Rathert, Jr. and Richard S. Bray. February 1952. 
45p. photos., diagrs., tab. (NACA RM A51J18) 



A CORRELATION BY MEANS OF THE TRANSONIC 
SIMILARITY RULES OF THE EXPERIMENTALLY 
DETERMINED CHAHACTEIOSTICS OF 22 RECTAN- 
GULAR WINGS OF SYMMETRICAL PROFILE. 
John B. McDevitt. February 1952. 60p. diagrs., 
3 tabs. (NACA RM A51L17b) 

FLUTTER INVESTIGATION OF TWO THIN, LOW- 
ASPECT-RATIO, SWEPT, SOLD), METAL WINGS 
IN THE TRANSONIC RANCaE BY USE OF A FRBE- 
FALLDJGBODY. W. T. Lauten, Jr. and Maurice 
A. Sylvester. February 1952. 12p. diagrs., photo., 
2 tabs. (NACA RM L51K28a) 

WIND-TUNNEL INVESTIGATION AT HIGH AND LOW 
SUBSONIC MACH NUMBERS OF A THIN SWEPT- 
BACK WING HAVING AN AIRFOIL SECTION DE- 
SIGNED FOR HIGH MAXIMUM LIFT. Stanley F. 
Racisz and Nicholas J. Paradiso. February 1952. 
46p. diagrs., photo., tab. (NACA RM L51L04) 

PRELIMINARY INVESTIGATION OF THE EFFECTS 
OF A PADDLE BALANCE ON THE CONTROL 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
TAPERED 45.58° SWEPTBACK WING OF ASPECT 
PATIO 3 HAVING A FULL-SPAN FLAP-TYPE CON- 
TROL. William C. Moseley, Jr. February 1952. 
24p. diagrs., photo. (NACA RM L51L19) 

HINGE -MOMENT AND OTHER AERODYNAMIC 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
QUARTER-SPAN SPOILER ON A TAPERED 45° 
SWEPTBACK WING OF ASPECT RATIO 3. 
Joseph E. Fikes. February 1952. 22p. diagrs., 
photo. (NACA RM L52A03) 

PRELIMINARY INVESTIGATION OF CONTROL 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3 HAVING A HORN-BALANCED FULL-SPAN 
CONTROL. John G. Lowry and Joseph E. Fikes. 
April 1952. 22p. diagrs., photo. (NACA RM 
L52A11) 

PRELIMINARY INVESTIGATION AT TRANSONIC 
SPEEDS OF THE EFFECT OF BALANCING TABS 
ON THE HINGE-MOMENT AND OTHER AEtlODY- 
NAMIC CHARACTERISTICS OF A FULL-SPAN FLAP 
ON A TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIOS. Vernard E. Lockwood and Joseph E. 
Fikes. April 1952. 27p. diagrs., photo., (NACA 
RM L52A23) 

THE EFFECTS ON THE AERODYNAMIC CHARAC- 
TERISTICS OF VARYING THE WING THICKNESS 
RATIO OF A TRIANGULAR WING-BODY CONFIG- 
URATION AT TRANSONIC SPEEDS FROM TESTS BY 
THE NACA WING-FLOW METHOD. Albert W. Hall 
and James M. McKay. April 1952. 27p. diagrs., 
photo., 2 tabs. (NACA RM L52B18) 

INVESTIGATION OF LIFT AND CENTER OF PRES- 
SURE OF LOW -ASPECT-RATIO, CRUCIFORM, 
TRIANGULAR, AND RECTANGULAR WINGS IN 
COMBINATION WITH A SLENDER FUSELAGE AT 
HIGH SUPERSONIC SPEEDS. Thomas N. Canning 
and Billy Pat Denardo. June 1952. 28p. diagrs., 
photos. (NACA RM A52C24) 

AN INVESTIGATION OF LONGITUDINAL CONTROL 
CHARACTERISTICS OF A WING-TIP CONTROL 
SURFACE ON A SWEPTBACK WING AT TRANSONIC 
SPEEDS BY THE NACA WING- FLOW METHOD. 
James P. Trant, Jr. June 1952. 23p. diagrs., 
photos., tab. (NACA RM L52B15a) 

SMALL-SCALE TRANSONIC INVESTIGATION OF 
THE EFFECTS OF PARTIAL-SPAN LEADING-EDGE 
CAMBER ON THE AERODYNAMIC CHARACTERIS- 
TICS OF A 50° 38' SWEPTBACK WING OF ASPECT 
RATIO 2.98. William J. Alford, Jr. and Andrew L. 
Byrnes, Jr. June 1952. 28p. diagrs., photo., tab. 
(NACA RM L52D08a) 



AERODYNAMICS 
WINGS (1.2} 



45 



Mach Number Effects - Complete 
Wings (Cont. ) 



THE TRANSONIC CHARACTERISTICS OF 38 CAM- 
BERED RECTANGULAR WINGS OF VARYING AS- 
PECT RATIO AND THICKNESS AS DETERMINED BY 
THE TRANSONIC-BUMP TECHNIQUE. Warren H. 
Nelson and Walter J. Krumm. July 1952. 173p. 
diagrs., photos. (NACA RM A52D11) 

PRELIMINARY STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTERIS- 
TICS OF THIN WINGS. A. Gerald Rainey. July 1952. 
33p. diagrs., photo., tab. (NACA RM L52D08) 

CONTROL' CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A LINKED FLAP AND SPOILER ON A 
TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3. Vernard E. Lockwood and Joseph E. 
Fikes. July 1952. 24p. diagrs., photo. (NACA 
RM L52D25) 

SMALL-SCALE TRANSONIC INVESTIGATION OF 
THE EFFECTS OF FULL-SPAN AND PARTIAL- 
SPAN LEADING-EDGE FLAPS ON THE AERO- 
DYNAMIC CHARACTERISTICS OF A 50° 38' SWEPT- 
BACK WING OF ASPECT RATIO 2.98. Kenneth P. 
Spreemann and William J. Alford, Jr. July 1952. 
31p. diagrs., photo. (NACA RM L52E12) 

LATERAL-CONTROL INVESTIGATION AT TRAN- 
SONIC SPEEDS OF RETRACTABLE SPOILER AND 
PLUG-TYPE SPOILER-SLOT AILERONS ON A 
TAPERED 60° SWEPTBACK WING OF ASPECT 
RATIO 2. TRANSONIC -BUMP METHOD. Alexander 
D. Hammond and James M. Watson. August 1952. 
19p. diagrs. (NACA RM L52F16) 

HINGE-MOMENT AND CONTROL-EFFECTIVENESS 
CHARACTERISTICS OF AN OUTBOARD FLAP WITH 
AN OVERHANG NOSE BALANCE ON A TAPERED 
35° SWEPTBACK WING O/t ASPECT RATIO 4. 
TRANSONIC -BUMP METHOD. Robert F. Thompson 
and William C. Moseley, Jr. Augiist 1952. 51p. 
diagrs. (NACA RM L52G08) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 60° DELTA WING EQUIPPED WITH A 
CONSTANT-CHORD FLAP-TYPE CONTROL WITH 
AND WITHOUT AN UNSHIELDED HORN BALANCE. 
TRANSONIC -BUMP METHOD. Harleth G. Wiley 
and Leon Zontek. September 1952. 25p. diagrs. 
(NACARM L51H22) 

FLIGHT MEASUREMENTS OF THE LATERAL STA- 
BILITY AND CONTROL CHARACTERISTICS OF A 
HIGH-SPEED FICHITER AIRPLANE. H. L. Crane, 
A. R. Beckhardt and C. E. Matheny. September 
1952. 50p. diagrs., tab. (NACA RM L52B14) 

AN APPLICATION OF THE ROCKET-PROPELLED- 
MODEL TECHNIQUE TO THE INVESTIGATION OF 
LOW-LIFT BUFFETING AND THE RESULTS OF 
PRELIMINARY TESTS. Homer P. Mason and 
William N. Gardner. September 1952. 19p. 
diagrs., photos. (NACA RM L52C27) 

FORCE TESTS OF THREE THIN WINGS OF MOD- 
ERATELY LOW ASPECT RATIO AT HIGH SUB- 
SONIC MACH NUMBERS. Gareth H. Jordan. 
October 1952. 22p. diagrs. (NACA RM L52I08) 

AN ANALYSIS OF ESTIMATED AND EXPERIMENT- 
AL TRANSONIC DOWNWASH CHARACTERISTICS 
AS AFFECTED BY PLAN FORM AND THICKNESS 
FOR WING AND WING-FUSELAGE CONFIGURA- 
TIONS. Joseph Weil, George S. Campbell and 
Margaret S. Diederich. November 1952. 92p. 
diagrs. , 2 tabs. (NACA RM L52I22) 



INVESTIGATION AT TRANSONIC SPEEDS OF THE 
EFFECT OF A POSITIVE-UFT BALANCING TAB 
ON THE HINGE -MOMENT AND LIFT CHARACTER- 
ISTICS OF A FULL-SPAN FLAP ON A TAPERED 
45° SWEPTBACK WING OF ASPECT RATIO 3. 
Vernard E. Lockwood and Joseph E. Fikes. 
November 1952. 22p. diagrs. , photo. (NACA 
RM L52J09) 

CORRELATION OF BUFFET BOUNDARIES PRE- 
DICTED FROM WIND-TUNNEL TESTS WITH THOSE 
MEASURED DURING FLIGHT TESTS ON THE F8F-1 
AND X-1 AIRPLANES - TRANSONIC -BUMP METH- 
OD. Andrew Martin and James F. Reed. 
December 1952. 22p. diagrs., photos., tab. 
(NACA RM A52J17) 

AERODYNAMIC CHARACTERBTICS OF TWO 
DELTA WINGS AT MACH NUMBER 4.04 AND COB- 
RELATIONS OF LIFT AND MINIMUM -DRAG DATA 
FOR DELTA WINGS AT MACH NUMBERS FROM 1.62 
TO 6.9. Edward F. Ulmann and Robert W. Dunning. 
December 1952. 20p. diagrs. (NACA RM L52K19) 

ON THE APPLICATION OF TRANSONIC SIMILARITY 
RULES TO WINGS OF FINITE SPAN. John R. 
Spreiter. 1953. ii, 21p. diagrs. (NACA Rept. 1153. 
Formerly TN 2726) 

EFFECTS OF ROUGHNESS AND REYNOLDS NUM- 
BER ON THE NONLINEAR LIFT CHARACTERISTICS 
OF A WING WITH MODIFIED HEXAGONAL AIRFOIL 
SECTIONS. Milton A. Schwartzberg. 
February 1953. 18p. diagrs., photo. (NACA 
RM L52L26a) 

INVESTIGATION OF THREE TAPERED 45° SWEPT- 
BACK CAMBERED AND TWISTED WINGS COVER- 
ING A SIMULTANEOUS VARIATION IN ASPECT 
RATIO AND THICKNESS RATIO AND OF ONE RE- 
LATED SYMMETRICAL WING AT TRANSONIC 
SPEEDS BY THE WING-FLOW METHOD. Harold I. 
Johnson. March 1953. 55p. diagrs., photos., 2 tabs. 
(NACA RM L52H07) 

MEASUREMENTS OF AERODYNAMIC CHAR- 
ACTERISTICS AT TRANSONIC SPEEDS OF AN 
UNSWEPT AND UNTAPERED NACA 65-009 AIR- 
FOIL MODEL OF ASPECT RATIO 3 WITH 1/4- 
CHORD PLAIN FLAP BY THE NACA WING-FLOW 
METHOD. Harold I. Johnson. June 1953. 35p. 
diagrs.. photo. (NACA RM L53D21) 

EFFECTS OF RATE OF FLAP DEFLECTION ON 
FLAP HINGE MOMENT AND WING LIFT THROUGH 
THE MACH NUMBER RANGE FROM 0.32 TO 0.87. 
Thomas R. Turner. June 1953. 29p. diagrs., 
photos. (NACA RM L53E11) 

SOME OBSERVATIONS ON STALL FLUTTER AND 
BUFFETING. A. Gerald Rainey. June 1953. lip. 
diagrs. (NACA RM L53E15) 

INVESTIGATION AT TRANSONIC SPEEDS OF THE 
HINGE-MOMENT AND LIFT-EFFECTIVENESS 
CHARACTERISTICS OF A SINGLE FLAP AND A 
TANDEM FLAP ON A 60° DELTA WING. Delwln 
R. Croom and Harleth G. Wiley. July 1953. 16p. , 
diagrs. (NACA RM L53E28a) 

A CORRELATION BY MEANS OF TRANSONIC 
SIMILARITY RULES OF THE EXPERIMENTALLY 
DETERMINED CHARACTERISTICS OF 18 CAM- 
BERED WINGS OF RECTANGULAR PLAN FORM. 
John B. McDevitt. September 1953. 57p. diagrs. 
(NACARM A53G31) 

THE AERODYNAMIC CHARACTERISTICS AT 
TRANSONIC SPEEDS OF AN ALL-MOVABLE, 
TAPERED, 45° SWEPTBACK, ASPECT-RATIO-4 
TAIL DEFLECTED ABOUT A SKEWED HINGE AXIS 
AND EQUIPPED WITH AN INSET UNBALANCING 
TAB. James M. Watson. September 1953. 40p. 
diagrs. (NACA RM L53H13) 



AERODYNAMICS 
46 WINGS (1.2) 



Mach Number Effects - Connplete 
Wings (Cont. ) 



AN INVESTIGATION OF THE USE OF ROCKET- 
POWERED MODELS FOR GUST-LOAD STUDIES 
WITH AN APPLICATION TO A TAILLESS SWEPT- 
WING MODEL AT TRANSONIC SPEEDS. A. James 
Vitale, H. Press and C. C. Shufflebarger. June 
1954. 36p. dlagrs., photos., tab. (NACATN3161) 

LIFT AND PITCHING MOMENT AT SUPERSONIC 
SPEEDS DUE TO CONSTANT VERTICAL ACCELER- 
ATION FOR THIN SWEPTBACK TAPERED WINGS 
WITH STREAMWISE TIPS. SUPERSONIC LEADING 
AND TRAILING EDGES. Isabella J. Cole and 
Kenneth MargoUs. July 1954. 67p. diagrs., 4 tabs. 
(NACA TN 3196) 

A PRELIMINARY FLIGHT INVESTIGATION OF AN 
OIL-FLOW TECHNIQUE FOR AIR-FLOW VISUALI- 
ZATION. Harold I. Johnson and Robert G. Mungall. 
October 1954. 33p. diagrs., photos. (NACA 
RM L54G14a) 

COMPARISON OF FLUTTER CALCULATIONS USING 
VARIOUS AERODYNAMIC COEFFICIENTS WITH 
EXPERIMENTAL RESULTS FOR SOME RECTANGU- 
LAR CANTILEVER WINGS AT MACH NUMBER 1.3. 
Herbert C. Nelson and Ruby A. Rainey. November 
1954. 22p. diagrs., 2 tabs. (NACA TN 3301) 

A SIMPLIFIED METHOD FOR CALCULATING 
AEROELASTIC EFFECTS ON THE ROLL OF AIR- 
CRAFT. John M. Hedgepeth, Paul G. Waner, Jr. 
and Robert J. Kell. March 1955. 26p. diagrs., 
4 tabs. (NACA TN 3370) 

TOTAL LIFT AND PITCHING MOMENT ON THIN 
ARROWHEAD WINGS OSCILLATING IN SUPERSONIC 
POTENTIAL FLOW. H. J. Cunningham. May 1955. 
43p. diagrs., 4 tabs. (NACA TN 3433) 



WAKE 
(1.2.2.7) 



HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE. LONGITUDINAL STABILITY AND CON- 
TROL OF THE D-558-1. John B. Wright. July 8, 
1948. 47p. diagrs., tab. (NACA RM L8C23) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE - DYNAMIC PRESSURE AND COMPARISON 
OF POINT AND EFFECTIVE DOWNWASH AT THE 
TAIL OF THE D-558-1. Harold L. Robinson. 
November 4, 1948. 27p. diagrs. (NACA RM L8H05) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Joseph Well and Kenneth W. Goodson. 
February 24, 1949. 28p. diagrs., photo., tab. 
(NACA RM L9A21) 

INVESTIGATION OF DOWNWASH AND WAKE CHAR- 
ACTERISTICS AT A MACH NUMBER OF 1.53. I - 
RECTANGULAR WING. Edward W. Perkins and 
Thomas N. Canning. March 1, 1949. 29p. diagrs. 
(NACA RM A8L16) 



AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER -CHORD LINE SWEPT BACK 35°, 
ASPECT RATIO 4, TAPER RATIO 0. 6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. William C. Sleeman, Jr. and Robert E. 
Becht. April 21, 1949. 29p. diagrs., photo., tab. 
(NACA RM L9B25) 

INVESTIGATION OF DOWNWASH AND WAKE CHAR- 
ACTERISTICS AT A MACH NUMBER OF 1.53. H - 
TRIANGULAR WING. Edward W. Perkins and 
Thomas N. Canning. June 6, 1949. 31p. diagrs. 
(NACA RM A9D20) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 4, TAPER RATIO 0.3, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC-BUMP 
METHOD. Boyd C. Myers, II and Thomas J. King, 
Jr. July 20, 1949. 28p. diagrs., photo., tab. 
(NACA RM L9E25) 

AERODYNAMIC CHARACTERISTICS OF A DELTA 
WING WITH LEADING EDGE SWEPT BACK 45°, 
ASPECT RATIO 4, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. WilUam 
C. Sleeman, Jr. and Robert E. Becht. September 6, 
1949. 29p. diagrs., photo., tab. (NACA 
RM L9G22a) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 60°, 
ASPECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Thomas J. King, Jr. and Boyd C. Myers, 
n. September 6, 1949. 32p. diagrs., photos., tab. 
(NACA RM L9G27) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH UNSWEPT QUARTER -CHORD LINE, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A006 
AIRFOIL SECTION. TRANSONIC -BUMP METHOD. 
Kenneth W. Goodson and William D. Morrison, Jr. 
October 21, 1949. 32p. diagrs., photos., tab. 
(NACA RM L9H22) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Kenneth W. Goodson and Albert G. Few, 
Jr. November 1, 1949. 34p. diagrs., photos., tab. 
(NACA RM L9I08) 

DOWNWASH IN VORTEX REGION BEHIND 
TRAPEZOIDAL-WING TIP AT MACH NUMBER 1.91. 
J. L. Cummings, H. Mirels and L. E. Baughman. 
November 10, 1949. 39p. diagrs., photos. (NACA 
RM E9H15) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 35°, 
ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. William C. Sleeman, Jr. and William D. 
Morrison, Jr. December 12, 1949. 32p. diagrs., 
photos., tab. (NACA RM LQKlOa) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 60°, 
ASPECT RATIO 2, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Boyd C. Myers, II and Thomas J. King, 
Jr. February 24, 1950. 31p. diagrs., photos., tab. 
(NACA RM L50A12) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 
65A009 AIRFOH. SECTION. TRANSONIC -BUMP 
METHOD. Kenneth P. Spreemann, William D. 
Morrison, Jr. and Thomas B. Pasteur, Jr. April 6, 
19'50. 33p. diagrs., photos., tab. (NACA 
RM L50B03a) 



AERODYNAMICS 
WINGS (1.2) 



47 



Wake - Complete Wings (Cont. ) 



AERODYNAMIC CHAHACTERISTICS OF A WING 
WITH UNSWEPT QUARTER-CHORD LINE, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A004 
AIRFOIL SECTION. TRANSONIC -BUMP METHOD. 
Boyd C. Myers, II and James W. Wiggins. May 8, 
1950. 31p. diagrs., photos., tab. (NACA 
RM L50C16) 

LOW -SPEED raVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AIRPLANE - LONGITUDINAL 
CHARACTERISTICS. Noel K. Delany and Nora-Lee 
F. Hayter. September 8, 1950. BOp. diagrs., 
photos., 2 tabs. (NACA RM A50G06) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AT HIGH-SUBSONIC SPEEDS OF TWO 
MODELS OF A TRANSONIC RESEARCH AIRPLANE 
WITH WINGS AND HORIZONTAL TAILS OF ASPECT 
RATIOS 4.2 AND 2. Arvo A. Luoma and John B. 
Wright. September 29, 1950. 134p. diagrs., photos., 

3 tabs. (NACA RM L50H07) 

DOWNWASH IN VORTEX REGION BEHIND RECTAN- 
GULAR HALF -WING AT MACH NUMBER 1.91. John 
L. Cummings and Rudolph C. Haefeli. October 26, 

1950. 43p. diagrs., photos., tab. (NACA 
RM E50H10) 

INVESTIGATION OF THE DOWNWASH AND WAKE 
BEHIND A TRIANGULAR WING OF ASPECT RATIO 

4 AT SUBSONIC AND SUPERSONIC MACH NUM- 
BERS. Harold J. Walker and Louis S. Stivers, Jr. 
December 12, 1950. 32p. diagrs. (NACA 

RM A50I14a) 

EXPERIMENTAL DOWNWASH AND WAKE CHAR- 
ACTERISTICS AT SUBSONIC AND SUPERSONIC 
MACH NUMBERS BEHIND AN UNSWEPT, TAPERED 
WING OF ASPECT RATIO 2.67 WITH LEADING- 
AND TRAILING-EDGE FLAPS. Harold J. Walker, 
Louis S. Stivers, Jr. and Luther Beard, Jr. 
April 20, 1951. 43p. diagrs. (NACA RM A51B16) 

AN EXPERIMENTAL STUDY AT MODERATE AND 
HIGH SUBSONIC SPEEDS OF THE FLOW OVER 
WINGS WITH 30° AND 45° OF SWEEPBACK IN 
CONJUNCTION WITH A FUSELAGE. Richard T. 
Whitcomb. June 15, 1951. 56p. diagrs., photos. 
(NACA RM L50K27) 

AN EXPERIMENTAL STUDY OF MODERATE AND 
HIGH SUBSONIC SPEEDS OF THE FLOW OVER 
WINGS WITH 30° AND 45° OF SWEEPFORWARD 
IN CONJUNCTION WITH A FUSELAGE. Richard T. 
Whitcomb. June 15, 1951. 47p. diagrs., photo. 
(NACA RM L50K28) 

AN EXPERIMENTAL STUDY OF MODERATE AND 
HIGH SUBSONIC SPEEDS OF THE FLOW OVER AN 
LiNSWEPT WING IN CONJUNCTION WITH A FUSE- 
LAGE. Richard T. Whitcomb. June 18, 1951. 35p. 
diagrs., photos. (NACA RM L50L07) 

INVESTIGATION OF A TRIANGULAR WING IN CON- 
JUNCTION WITH A FUSELAGE AND HORIZONTAL 
TAIL TO DETERMINE DOWNWASH AND LONGITU- 
DINAL STABILITY CHARACTERISTICS - TRAN- 
SONIC BUMP METHOD. Edwin C. AUen. August 

1951. 22p. diagrs., photos. (NACA RM A51F12a) 

EFFECTS OF HORIZONTAL-TAIL POSITION, AREA, 
AND ASPECT RATIO ON LOW -SPEED STATIC 
LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A 60° TRLANGULAR-WING 
MODEL HAVING VARIOUS TRIANGULAR -ALL- 
MOVABLE HORIZONTAL TAILS. Byron M. Jaquet. 
December 1951. 61p. diagrs., photo., tab. (NACA 
RM L51I06) 



EFFECTS OF HORIZONTAL-TAIL POSITION AND 
ASPECT RATIO ON LOW-SPEED STATIC LONGI- 
TUDINAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF A 60° TRIANGULAR -WING MODEL HAV- 
ING TWIN TRIANGULAR ALL -MOVABLE TAILS. 
Byron M. Jaquet. May 1952. 45p. diagrs., photos. 
(NACA RM L52B25) 

A STUDY OF THE FLOW FIELD BEHIND THE TRI- 
ANGULAR HORIZONTAL TAIL OF A CANARD AIR- 
PLANE AT APPROXIMATELY THE VERTICAL- 
TAIL LOCATION BY MEANS OF A TUFT GRID. 
Joseph L. Johnson, Jr. October 1952. ISp. diagrs., 
tab. (NACA RM L52H11) 

AN ANAL-raiS OF ESTIMATED AND EXPERIMENT- 
AL TRANSONIC DOWNWASH CHARACTERISTICS 
AS AFFECTED BY PLAN FORM AND THICKNESS 
FOR WING AND WING-FUSELAGE CONFIGURA- 
TIONS. Joseph Weil, George S. Campbell and 
Margaret S. Diederieh. November 1952. 92p. 
diagrs. , 2 tabs. (NACA RM L52I22) 

CORRELATION OF BUFFET BOUNDARIES PRE- 
DICTED FROM WIND-TUNNEL TESTS WITH THOSE 
MEASURED DURING FLIGHT TESTS ON THE F8F-1 
AND X-1 AIRPLANES - TRANSONIC-BUMP METH- 
OD. Andrew Martin and James F. Reed. 
December 1952. 22p. diagrs., photos., tab. 
(NACA RM A52J17) 

APPLICATION OF TWO-DIMENSIONAL VORTEX 
THEORY TO THE PREDICTION OF FLOW FIELDS 
BEHIND WINGS OF WING-BODY COMBINATIONS 
AT SUBSONIC AND SUPERSONIC SPEEDS. Arthur 
Wm. Rogers. September 1954. (ii), 91p. diagrs., 
photo., 3 tabs. (NACA TN 3227) 

PRELIMINARY RESULTS FROM FLOW-FIELD 
MEASUREMENTS AROUND SINGLE AND TANDEM 
ROTORS IN THE LANGLEY FULL-SCALE TUNNEL. 
Harry H. Heyson. November 1954. 19p. diagrs., 
photos. (NACA TN 3242) 

PREDICTION OF DOWNWASH BEHIND SWEPT -WING 
AIRPLANES AT SUBSONIC SPEED. John De Young 
and Walter H. Barling, Jr. January 1955. 104p. 
diagrs., 3 tabs. (NACA TN 3346) 

FLIGHT MEASUREMENTS OF THE VELOCITY 
DISTRIBUTION AND PERSISTENCE OF THE 
TRAILING VORTICES OF AN AIRPLANE. 
Christopher C. Kraft, Jr. March 1955. 32p. 
diagrs., photos., tab. (NACA TN 3377) 

ON SLENDER DELTA WINGS WITH LEADING-EDGE 
SEPARATION. Clinton E. Brown and William H. 
Michael, Jr. April 1955. 27p. diagrs. (NACA 
TN 3430) 

BOUNDARY LAYER 
(1.2.2.8) 

WIND-TUNNEL INVESTIGATION OF A WING- 
FUSELAGE COMBINATION WITH EXTERNAL 
STORES. H. Norman Silvers and Kenneth P. 
Spreemann. July 9, 1948. 55p. diagrs. (NACA 
RM L7K20) 

INVESTIGATIONS AT SUPERSONIC SPEEDS OF 22 
TRIANGULAR WINGS REPRESENTING TWO AIR- 
FOIL SECTIONS FOR EACH OF 11 APEX ANGLES. 
Eugene S. Love. May 10, 1949. lOOp. diagrs., 
photos., 3 tabs. (NACA RM L9D07) 

INVESTIGATION AT MACH NUMBER 1.62 OF THE 
PRESSURE DISTRIBUTION OVER A RECTANGULAR 
WING WITH SYMMETRICAL CIRCULAR-ARC SEC- 
TION AND 30-PERCENT-CHORD TRAILING-EDGE 
FLAP. K. R. Czarnecki and James N. Mueller. 
January 25, 1950. 81p. diagrs., photos. (NACA 
RM L9J05) 



AERODYNAMICS 
48 WINGS (1.2) 



Characteristic s 
(1.2.2.8.1) 

A PRELIMINARY FLIGHT INVESTIGATION OF AN 
OIL-FLOW TECHNIQUE FOR AIR-FLOW VISUALI- 
ZATION. Harold I. Johnson and Robert G. Mungall. 
October 1954. 33p. diagrs., photos. (NACA 
RM L54G14a) 



Control 



(1.2.2.8.2) 



FLIGHT DETERMINATION OF THE EFFECTS OF 
WING VORTEX GENERATORS ON THE AERO- 
DYNAMIC CHARACTERISTICS OF THE DOUGLAS 
D-558-I AIRPLANE. De E. Beeler, Donald R. 
Bellman and John H. Griffith. August 14, 1951. 23p. 
diagrs., photos., tab. (NACA RM L51A23) 



EXPERIMENTAL INVESTIGATION OF AIR-FLOW 
UNIFORMITY AND PRESSURE LEVEL ON WIRE 
CLOTH FOR TRANSPIRATION-COOLING APPLICA- 
TIONS. Patrick L. Donoughe and Roy A. McKinnon. 
July 1952. 28p. diagrs., photos., tab. (NACA 
RM E52E16) 

A FIBROUS-GLA^ COMPACT AS A PERMEABLE 
MATERIAL FOR BOUNDARY -LAYER-CONTROL 
APPLICATIONS USING AREA SUCTION. Robert E. 
Dannenberg, James A. Weiberg and Bruno J. 
Gambucci. January 1955. 20p. diagrs., photos., 
2 tabs. (NACA TN 3388) 



AERODYNAMICS 49 



Bodies 

(1.3) 



AN EMPIRICAL CRITERION FOR FIN STABI- 
LIZING JETTISONABLE NOSE SECTIONS OF AIR- 
PLANES. Stanley H. Scher. December 8, 1949. 
21p. diagrs., photo., tab. (NACA RM L9I28) 



THE PATH AND MOTION OF SCALE MODELS OF 
JETTISONABLE NOSE SECTIONS AT SUPERSONIC 
SPEEDS AS DETERMINED FROM AN INVESTIGA- 
TION IN THE LANGLEY FREE-FLIGHT APPARA- 
TUS. Lawrence J. Gale. May 23, 1950. 35p. 
diagrs., photos., 2 tabs. (NACA RM L9J13a) 



MOTION OF A TRANSONIC AIRPLANE NOSE SEC- 
TION WHEN JETTISONED AS DETERMINED FROM 
WIND-TUNNEL INVESTIGATIONS ON A 1/25-SCALE 
MODEL. Stanley H. Scher and Lawrence J. Gale. 
May 26, 1950. 64p. diagrs., photos., tab. (NACA 
RM L9L08a) 



THE CALCULATION OF THE PATH OF A JETTI- 
SONABLE NOSE SECTION. Roscoe H. Goodwin. 
September 7, 1950. 35p. diagrs. (NACA RM L50G18) 



ESTIMATED DECELERATION OF AIRPLANE NOSE 
SECTION JETTISONED AT VARIOUS ALTITUDES 
AND AIRSPEEDS. Stanley H. Scher. January 8, 
1951. 39p. diagrs. (NACA RM L50K09) 



THE EFFECT OF BLUNTNESS ON THE DRAG OF 
SPHERICAL-TIPPED TRUNCATED CONES OF 
FINENESS RATIO 3 AT MACH NUMBERS 1.2 TO 
7.4. Simon C. Sommer and James A. Stark. April 
1952. IBp. photos., diagrs. (NACA RM A52B13) 



PRESSURE DISTRIBUTIONS ON BODIES OF REVO- 
LUTION AT SUBSONIC AND TRANSONIC SPEEDS. 
Richard L Cole. July 1952. 47p. diagrs., photos., 
tab. (NACA RM L52D30) 



INVESTIGATION OF THE VARIATION WITH 
REYNOLDS NUMBER OF THE BASE, WAVE, AND 
SKIN-FRICTION DRAG OF A PARABOLIC BODY OF 
REVOLUTION (NACA RM-10) AT MACH NUMBERS 
OF 1.62, 1.93, AND 2.41 IN THE LANGLEY 9-INCH 
SUPERSONIC TUNNEL. Eugene S. Love, Donald E. 
Coletti and August F. Bromra, Jr. October 1952. 
62p. diagrs., photos., (NACA RM L52K21) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF VARIOUS DORSAL-FIN AND VERTICAL-TAIL 
CONFIGURATIONS ON THE DIRECTIONAL STABIL- 
ITY OF A STREAMLINED BODY OF TRANSONIC 
SPEEDS. TRANSONIC -BUMP METHOD. Harold S. 
Johnson and William C. Hayes. April 1953. 22p. 
diagrs., photo., tab. (NACA RM L53B19) 



THE ZERO-LIFT DRAG OF A SLENDER BODY OF 
REVOLUTION (NACA RM-10 RESEARCH MODEL) 
AS DETERMINED FROM TESTS IN SEVERAL WIND 
TUNNELS AND IN FLIGHT AT SUPERSONIC 
SPEEDS. Albert J. Evans. 1954. ii, 13p. 
diagrs., tab. (NACA Rept. 1160. Formerly 
TN 2944) 



SOME NEW DRAG DATA ON THE NACA RM-10 
MISSILE AND A CORRELATION OF THE EXISTING 
DRAG MEASUREMENTS AT M = 1.6 AND 3.0. 
Robert J. Garros and Carlton S. James. June 1954. 
24p. diagrs., photos., tab. (NACA TN 3171) 

TRANSONIC FLOW PAST CONE CYLINDERS. 
George E. Solomon, California Institute of Technology. 
September 1954. 56p. diagrs., photos. (NACA 
TN 3213) 

AN EXPERIMENTAL INVESTIGATION OF THE 
BASE PRESSURE CHARACTERISTICS OF NON- 
LIFTING BODIES OF REVOLUTION AT MACH 
NUMBERS FROM 2.73 TO 4.98. John O. Roller, Jr. 
and Frank M. Hamaker. March 1955. 45p. diagrs., 
photos. (NACA TN 3393. Formerly RM A52E20) 



THEORY 
(1.3.1) 



ERROR IN AIRSPEED MEASUREMENT DUE TO 
STATIC -PRESSURE FIELD AHEAD OF SHARP- 
NOSE BODIES OF REVOLUTION AT TRANSONIC 
SPEEDS. Edward C. B. Danforth and J. Ford 
Johnston. August 19, 1949. 31p. diagrs., photos. 
(NACA RM L9C25) 

MEASUREMENTS OF THE DRAG AND PRESSURE 
DISTRIBUTION ON A BODY OF REVOLUTION 
THROUGHOUT TRANSITION FROM SUBSONIC TO 
SUPERSONIC SPEEDS. Jim Rogers Thompson. 
January 16, 1950. 36p. diagrs., photos., 2 tabs. 
(NACA RM L9J27) 

LOW -SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AIRPLANE - LONGITUDINAL 
CHARACTERBTICS. Noel K. Delany and Nora-Lee 
F. Hayter. September 8, 1950. 80p. diagrs., 
photos., 2 tabs. (NACA RM A50G06) 

AVERAGE SKIN-FRICTION COEFFICIENTS FROM 
BOUNDARY-LAYER MEASUREMENTS IN FLIGHT 
ON A PARABOLIC BODY OF REVOLUTION (NACA 
RM-10) AT SUPERSONIC SPEEDS AND AT LARGE 
REYNOLDS NUMBERS. Charles B. Rumsey and J. 
Dan Loposer. March 7, 1951. 33p. diagrs., photo. 
(NACA RM L51B12) 

A SEMIEMPIRICAL METHOD FOR CALCULATING 
THE PITCHING MOMENT OF BODIES OF REVO- 
LUTION AT LOW MACH NUMBERS. Edward J. 
Hopkins. May 17, 1951. 27p. diagrs., tab. (NACA 
RM A51C14) 

AN EXPERIMENTAL INVESTIGATION AT SUBSONIC 
SPEEDS OF A SCOOP -TYPE AIR -INDUCTION 
SYSTEM FOR A SUPERSONIC AIRPLANE. Curt A. 
Holzhauser. July 1951. 45p. diagrs., photos. (NACA 
RM A51E24) 



50 



AERODYNAMICS 
BODIES (1. 3) 



Theory - Bodies (Cont. ) 



A SUMMARY OF AVAILABLE KNOWLEDGE CON- 
CERNING SKIN FRICTION AND HEAT TRANSFER 
AND ns APPLICATION TO THE DESIGN OF HIGH- 
SPEED MISSILES. Morris W. Rubesin, Charles B. 
Rumsey and Steven A. Varga. November 1951. 17p. 
diagrs. (NACA RM A51J25a) 

BODIES OF REVOLUTION FOR MINIMUM DRAG AT 
HIGH SUPERSONIC AIRSPEEDS. A. J. Eggers, Jr., 
David H. Dennis and Meyer M. Resnilioft. February 
1952. 44p. diagrs., photos. (NACA RM A51K27) 



PRELIMINARy INVESTIGATION OF THE DRAG 
CHARACTERISTICS OF THE NACA RM-10 MISSILE 
AT MACH NUMBERS OF 1.40 AND 1.59 IN THE 
LANGLEY 4- BY 4-FOOT SUPERSONIC TUNNEL. 
Lowell E. Basel, Archibald R. Sinclair and Clyde V. 
Hamilton, April 1952. 49p. diagrs., photos, 3 tabs. 
(NACA RM L52A14) 

SUPPLEMENTAKY NOTE ON MODIFIED -IMPACT - 
THEORY CALCULATIONS FOR BODIES OF REVO- 
LUTION HAVING MINIMUM DRAG AT HYPERSONIC 
SPEEDS. Meyer M. ResnikoH. July 1952. 13p. 
diagr. (NACA RM A52D24) 

PRESSURE DISTRIBUTIONS ON BODIES OF REVO- 
LUTION AT SUBSONIC AND TRANSONIC SPEEDS. 
Richard I. Cole. July 1952. 47p. diagrs., photos., 
tab. (NACA RM L52D30) 

A VECTOR STUDY OF LINEARIZED SUPERSONIC 
FLOW APPLICATIONS TO NONPLANAR 
PROBLEMS. John C. Martin. 1953. ii, 34p. 
diagrs., tab. (NACA Rept. 1143. Formerly 
TN 2641) 

A NEW HODOGRAPH FOR FREE -STREAMLINE 
THEORY. Anatol Roshko, California Institute of 
Technology. July 1954. 39p. diagrs., 3 tabs. 
(NACA TN 3168) 

ON THE DRAG AND SHEDDING FREQUENCY OF 
TWO-DIMENSIONAL BLUFF BODIES. Anatol 
Roshko, California Institute of Technology. 
July 1954. 29p. diagrs., tab. (NACA TN 3169) 

THEORETICAL INVESTIGATION AT SUBSONIC 
SPEEDS OF THE FLOW AHEAD OF A SLENDER 
INCLINED PARABOLIC -ARC BODY OF REVOLU- 
TION AND CORRELATION WITH EXPERIMENTAL 
DATA OBTAINED AT LOW SPEEDS. William Letko 
and Edward C. B. Danforth, m. July 1954. 56p. 
diagrs. (NACA TN 3205) 

ON THE DETERMINATION OF CERTAIN BASIC 
TYPES OF SUPERSONIC FLOW FIELDS. (Sulla 
determinazione di alcuni tlpi di campi di corrente 
ipersonora). Carlo Ferrari. November 1954. 17p. 
diagrs. (NACA TM 1381. Trans, from Rendlconti 
delta R. Accademie Nazionale del Lincei, Series 8, 
V. 7, no. 6, Dec. 1949) 

SUBSONIC EDGES IN THIN-WING AND SLENDER- 
BODY THEORY. Milton D. Van Dyke. November 
1954. 26p. diagrs. (NACA TN 3343) 

ARRANGEMENT OF FUSIFORM BODIES TO RE- 
DUCE THE WAVE DRAG AT SUPERSONIC SPEEDS. 
Morris D. Friedman and Doris Cohen. November 
1954 23p. diagrs. (NACA TN 3345. Formerly 
RM A51I20) 



GENERAL THEORY OF CONICAL FLOWS AND ITS 
APPLICATION TO SUPERSONIC AERODYNAMICS. 
(La theorie gene'rale des mouvements coniques et 
ses applications a I'aerodynamique supersonlque). 
Paul Germain. PREFACE. M. J. Peres. 
January 1955. vii, 333p. diagrs. (NACA 
TM 1354. Trans, from Office National d'itudes et 
de Recherches Aeronautiques, Pub. 34, 1949) 

MINIMUM -DRAG BODIES OF REVOLUTION IN A 
NONUNIFORM SUPERSONIC FLOW FIELD. Conrad 
Rennemann, Jr. February 1955. 25p. diagrs. 
(NACA TN 3369) 

AXULLY SYMMETRIC SHAPES WITH MINIMUM 
WAVE DRAG. Max. A. Heaslet and Franklyn B. 
Fuller. February 1955. 46p. diagrs. (NACA 
TN 3389) 

APPLICATION OF THE GENERALIZED SHOCK- 
EXPANSION METHOD TO INCLINED BODIES OF 
REVOLUTION TRAVELING AT HIGH SUPERSONIC 
AIRSPEEDS. Raymond C. Savin. April 1955. 
71p. diagrs., photos., tab. (NACA TN 3349) 



SHAPE VARIABLES 
(1.3.2) 



THE EFFECT OF REAR CHINE STRIPS ON THE 
TAKE-OFF CHARACTERISTICS OF A HIGH-SPEED 
AIRPLANE FITTED WITH NACA HYDRO-SKIS. 
John A. Ramsen. March 17, 1949. 7p. diagrs., 
photo. (NACA RM L9B10a) 

PRELIMINARY WIND-TUNNEL INVESTIGATION AT 
HIGH -SUBSONIC SPEEDS OF PLANDJG-TAIL, 
BLENDED, AND AIRFOIL-FOREBODY SWEPT 
HULLS. John M. Riebe and Richard G. MacLeod. 
September 12, 1949. 33p. diagrs., photos., 3 tabs. 
(NACA RM L9D01) 

EXPERIMENTAL INVESTIGATION OF SUPERSONIC 
FLOW WITH DETACHED SHOCK WAVES FOR 
MACH NUMBERS BETWEEN 1.8 AND 2.9. W. E. 
Moeckel. July 5, 1950. 56p, diagrs., photos., 4 
tabs. (NACA RM E50I^05) 

STATIC DIRECTIONAL STABILITY OF A TANDEM- 
HEUCOPTER FUSELAGE. Charles C. Smith, Jr. 
August 9, 1950. 23p. diagrs., photo. (NACA 
RM L50F29) 

FUGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.8 TO 1.5 TO DETERMINE THE EFFECTS 
OF NOSE BLUNTNESS ON THE TOTAL DRAG OF 
TWO FIN-STABILIZED BODIES OF REVOLUTION. 
Roger G. Hart. October 16, 1950. 12p. diagrs., 
photos., 2 talJS. (NACA RM L50I08a) 

RESULTS OF FLIGHT TESTS TO DETERMINE 
DRAG OF PARABOLIC AND CONE-CYLINDER 
BODIES OF VERY LARGE FINENESS RATIOS AT 
SUPERSONIC SPEEDS. Clement J. Welsh and 
Carlos A. deMoraes. August 1951. 17p. diagrs., 
photos. (NACA RM L51E18) 

PRESSURE DISTRIBUTIONS ON BODIES OF REVO- 
LUTION AT SUBSONIC AND TRANSONIC SPEEDS. 
Richard L Cole. July 1952. 47p. diagrs., photos., 
tab. (NACA RM L52D30) 



AERODYNAMICS 
BODIES (1.3) 



51 



Shape Variables - Bodies (Cont. ) 

AVERAGE SKIN-FRICTION COEFFICIENTS FROM 
BOUNDARY-LAYER MEASUREMENTS ON A OGIVE- 
CYLINDER BODY IN FLIGHT AT SUPERSONIC 
SPEEDS. J. Dan Loposer. January 1953. lip. 
djagrs., photo. (NACA RM L52K28a) 



REDUCTION OF HELICOPTER PARASITE DRAG. 
Robert D. Harrington. August 1954. 8p. diagrs. 
(NACA TN 3234) 

EXPERIMENTAL DETERMINATION OF BOUNDARY- 
LAYER TRANSITION ON A BODY OF REVOLUTION 
AT M = 3.5. James R. Jedllcka, Max E. WUklns 
and Alvin Seiff. October 1954. 56p. diagrs., photos. 
(NACA TN 3342. Formerly RM A53L18) 

MINIMUM -DRAG BODIES OF REVOLUTION IN A 
NONUNIFORM SUPERSONIC FLOW FIELD. Conrad 
Rennemann, Jr. February 1955. 25p. diagrs. 
(NACA TN 3369) 

APPLICATION OF THE GENERALIZED SHOCK- 
EXPANSION METHOD TO INCLINED BODIES OF 
REVOLUTION TRAVELING AT HIGH SUPERSONIC 
AIRSPEEDS. Raymond C. Savin. April 1955. 
71p. diagrs., photos., tab. (NACA TN 3349) 

FLIGHT MEASUREMENTS OF BASE PRESSURE ON 
BODIES OF REVOLUTION WITH AND WITHOUT 
SIMULATED ROCKET CHAMBERS. Robert F. Peck. 
April 1955. 18p. diagrs., photo. (NACA TN 3372. 
Formerly RM L50I28a) 



FINENESS RATIO 
(1.3.2. 1) 



FUGHT TESTS TO DETERMINE THE DRAG OF 
FIN-STABILIZED PARABOLIC BODIES AT TRAN- 
SONIC AND SUPERSONIC SPEEDS. Sidney R. 
Alexander, Leo T. ChauvLn and Charles B. Rumsey. 
April 21, 1948. 24p. diagrs., photos. (NACA 
RM L8A05) 

DRAG MEASUREMENTS AT TRANSONIC SPEEDS 
OF TWO BODIES OF FINENESS RATIO 9 WITH 
DIFFERENT LOCATIONS OF MAXIMUM BODY 
DIAMETER. Jim Rogers Thompson and Max C. 
Kurbjun. July 22, 1948. 17p. diagrs., photos. 
(NACA RM L8A28b) 

EFFECT OF WING SWEEP, TAPER, AND THICK- 
NESS RATIO ON THE TRANSONIC DRAG CHARAC- 
TERISTICS OF WING-BODY COMBINATIONS. Jim 
Rogers Thompson and Charles W. Mathews. 
December 31, 1948. 29p. diagrs., photos., 2 tabs. 
(NACA RM L8K01) 

ERROR IN AIRSPEED MEASUREMENT DUE TO 
STATIC-PRESSURE FIELD AHEAD OF SHARP- 
NOSE BODIES OF REVOLUTION AT TRANSONIC 
SPEEDS. Edward C. B. Danforth and J. Ford 
Johnston. August 19, 1949. 31p. diagrs., photos. 
(NACA RM L9C25) 



AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBSR OF 1.25 OF A 6-PERCENT-THICK TRIAN- 
GULAR WING AND 6- AND 9-PERCENT-THICK TRI- 
.WGULAR WINGS IN COMBINATION WITH A FUSE- 
LAGE. WING ASPECT RATIO 2.31, BICONVEX AIR- 
FOIL SECTIONS. Albert W. Hall and Garland J. 
Morris. May 5, 1950. 22p. diagrs., photo., 2 tabs. 
(NACA RM L50D05) 



INVESTIGATION AT TRANSONIC SPEEDS OF A 
35-PEHCENT-CHORD AILERON ON A TAPERED 
WEDGE -TYPE WING OF ASPECT RATIO 2.5 WITH 
AND WITHOUT A FUSELAGE. Thomas R. Turner 
and Joseph E. Fikes. September 8, 1950. 25p. 
diagrs. (NACA RM L50G13a) 



APPARATUS FOR OBTAINING A SUPERSONIC 
FLOW OF VERY SHORT DURATION AND SOME 
DRAG MEASUREMENTS OBTAINED WITH ITS USE. 
John E. Yeates, Jr. , F. J. Bailey, Jr. and T. J. 
Voglewede. July 23, 1951. 23p. diagrs., photos. 
(NACA RM L9C01) 



WING-FLOW STUDY OF PRESSURE -DRAG REDUC- 
TION AT TRANSONIC SPEED BY PROJECTING A 
JET OF AIR FROM THE NOSE OF A PROLATE 
SPHEROID OF FINENESS RATIO 6. Mitchell 
Lopatoff. October 1951. 20p. photos., diagrs., tab. 
(NACA RM L51E09) 



BASE PRESSURES MEASURED ON SEVERAL 
PARABOLIC -ARC BODIES OF REVOLUTION IN 
FREE FLIGHT AT MACH NUMBERS FROM 0.8 TO 
1.4 AND AT LARGE REYNOLDS NUMBERS. Ellis 
Katz and William E. Stoney, Jr. October 1951. 20p. 
diagrs., photos. (NACA RM L51F29) 



PRESSURE DISTRIBUTIONS ON BODIES OF REVO- 
LUTION AT SUBSONIC AND TRANSONIC SPEEDS. 
Richard I. Cole. July 1952. 47p. diagrs., photos., 
tab. (NACA RM L52D30) 



AERODYNAMIC CHARACTERISTICS OF A REFINED 
DEEP-STEP PLANING-TAIL FLYING-BOAT HULL 
WITH VARIOUS FOREBODY AND AFTERBODY 
SHAPES. John M. Riebe and Rodger L. Naeseth. 
1953. ii, 19p. diagrs., photos., 8 tabs. (NACA 
Rept. 1144. Formerly TN 2489; RM L8F01) 

A COMPARISON OF THE EXPERIMENTAL SUB- 
SONIC PRESSURE DISTRIBUTIONS ABOUT SEV- 
ERAL BODIES OF REVOLUTION WITH PRESSURE 
DISTRIBUTIONS COMPUTED BY MEANS OF THE 
LINEARIZED THEORY. Clarence W. Matthews. 
1953. ii, 29p. diagrs., tab. (NACA Rept. 1155. 
Formerly TN 2519; RM L9F28) 

GENERAL THEORY OF CONICAL FLOWS AND ITS 
APPLICATION TO SUPERSONIC AERODYNAMICS. 
(La theorie generale des mouvements coniques at 
ses applications a I'aerodynamique supersonique). 
Paul Germain. PREFACE. M. J. Peres. 
January 1955. vii, 333p. diagrs. (NACA 
TM 1354. Trans, from Office National d'fetudes et 
de Recherches Aeronautiques, Pub. 34, 1949) 



STATIC STABILITY OF FUSELAGES HAVING A 
RELATIVELY FLAT CROSS SECTION. William R. 
Bates. March 1955. 29p. diagrs., tab. (NACA 
TN 3429. Formerly RM L9I06a) 



AERODYNAMICS 
52 BODIES (1.3) 



CROSS SECTION 
(1. 3.2.2) 



DAMPING EN YAW AND STATIC DIRECTIONAL 
STABILITY OF A CANARD AIRPLANE MODEL AND 
OF SEVERAL MODELS HAVING FUSELAGES OF 
RELATIVELY FLAT CROSS SECTION. Joseph L. 
Johnson. October 16, 1950. 20p. diagrs., tab. 
(NACA RM L50H30a) 

FREE-FLIGHT-TUNNEL INVESTIGATION OF THE 
LOW -SPEED STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A MODEL HAVING A FUSELAGE 
OR RELATIVELY FLAT CROSS SECTION. John W. 
Paulson and Joseph L. Johnson, Jr. February 1953. 
SOp. diagrs., photo., tab. (NACA RM L52L22) 

STATIC STABILITY OF FUSELAGES HAVING A 
RELATIVELY FLAT CROSS SECTION. William R. 
Bates. March 1955. 29p. diagrs., tab. {NACA 
TN 3429. Formerly RM L9I06a) 



THICKNESS DISTRIBUTION 
(1.3.2.3) 



DRAG MEASUREMENTS AT TRANSONIC SPEEDS 
OF TWO BODIES OF FINENESS RATIO 9 WITH 
DIFFERENT LOCATIONS OF MAXIMUM BODY 
DIAMETER. Jim Rogers Thompson and Max C. 
Kurbjun. July 22, 1948. 17p. diagrs., photos. 
(NACA RM L8A28b) 



STUDY BY NACA WING-FLOW METHOD OF 
TRANSONIC DRAG CHARACTERISTICS OF A 
BLUNT-NOSE BODY OF REVOLUTION AND COM- 
PARISON WITH RESULTS FOR A SHARP -NOSE 
BODY. J. Ford Johnston and Mitchell Lopatoft. 
April 26, 1949. 26p. diagrs., photos. (NACA 
RM L9C11) 



MEASUREMENTS OF THE DRAG AND PRESSURE 
DISTRIBUTION ON A BODY OF REVOLUTION 
THROUGHOUT TRANSITION FROM SUBSONIC TO 
SUPERSONIC SPEEDS. Jim Rogers Thompson. 
January 16, 1950. 36p. diagrs., photos., 2 tabs. 
(NACA RM L9J27) 



FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.8 TO 1.5 TO DETERMINE THE EFFECTS 
OF NOSE BLUNTNESS ON THE TOTAL DRAG OF 
TWO FIN-STABILIZED BODIES OF REVOLUTION. 
Roger G. Hart. October 16, 1950. 12p. diagrs., 
photos., 2 tabs. (NACA RM L50I08a) 



BASE PRESSURES MEASURED ON SEVERAL 
PARABOLIC -ARC BODIES OF REVOLUTION IN 
FREE FLIGHT AT MACH NUMBERS FROM 0.8 TO 
1.4 AND AT LARGE REYNOLDS NUMBERS. Ellis 
Katz and William E. Stoney, Jr. October 1951. 20p. 
diagrs., photos. (NACA RM L51F29) 



AN EXPLORATORY INVESTIGATION OF SKIN 
FRICTION AND TRANSITION ON THREE BODIES 
OF REVOLUTION AT A MACH NUMBER OF 1.61. 
John H. Hilton, Jr. and K. R. Czarnecki. June 
1954. 15p. diagrs. (NACA TN 3193) 



SURFACE CONDITIONS 
(1.3.2.4) 



WING-FLOW STUDY OF PRESSURE-DRAG REDUC- 
TION AT TRANSONIC SPEED BY PROJECTING A 
JET OF AIR FROM THE NOSE OF A PROLATE 
SPHEROID OF FINENESS RATIO 6. Mitchell 
Lopatoff. October 1951. 20p. photos., diagrs., tab. 
(NACA RM L51E09) 

FLIGHT MEASUREMENTS OF THE EFFECTS OF 
SURFACE CONDITION ON THE SUPERSONIC DRAG 
OF FIN-STABILIZED PARABOLIC BODIES OF REV- 
OLUTION. H. Herbert Jackson. May 1952. 17p. 
diagrs., photos. (NACA RM L52B26) 

INVESTIGATION OF THE VARIATION WITH 
REYNOLDS NUMBER OF THE BASE, WAVE, AND 
SKIN -FRICTION DRAG OF A PARABOLIC BODY OF 
REVOLUTION (NACA RM-10) AT MACH NUMBERS 
OF 1.62, 1.93, AND 2.41 IN THE LANGLEY 9-INCH 
SUPERSONIC TUNNEL. Eugene S. Love, Donald E. 
Coletti and August F. Bromm, Jr. October 1952. 
62p. diagrs., photos., (NACA RM L52H21) 

INVESTIGATION OF DISTRIBUTED SURFACE 
ROUGHNESS ON A BODY OF REVOLUTION AT A 
MACH NUMBER OF 1.61. K. R. Czarnecki, Ross 
B. Robinson and John H. Hilton, Jr. June 1954. 
35p. diagrs., photo., 2 tabs. (NACA TN 3230) 

EXPERIMENTAL DETERMINATION OF BOUNDARY - 
LAYER TRANSITION ON A, BODY OF REVOLUTION 
AT M = 3.5. James R. Jedlicka, Max E. Wilkins 
and Alvin Seiff. October 1954. 56p. diagrs., photos. 
(NACA TN 3342. Formerly RM A53L18) 

BOUNDARY-LAYER TRANSITION AT MACH 3.12 
WITH AND WITHOUT SINGLE ROUGHNESS 
ELEMENTS. Paul F. Brinich. December 1954. 
41 p. diagrs. (NACA TN 3267) 



PROTUBERANCES 
(1.3.2. 5) 



LOW -SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AIRPLANE - LONGITUDINAL 
CHARACTERISTICS. Noel K. Delany and Nora-Lee 
F. Hayter. September 8, 1950. 80p. diagrs., 
photos., 2 tabs. (NACA RM A50G06) 



DRAG INVESTIGATION OF SOME FIN CONFIGURA- 
TIONS FOR BOOSTER ROCKETS AT MACH NUM- 
BERS BETWEEN 0.5 AND 1.4. John C. McFall, Jr. 
November 21, 1950. 17p. diagrs., photos., tab. 
(NACA RM L50J12) 



FLIGHT MEASUREMENTS OF THE EFFECTS OF 
SURFACE CONDITION ON THE SUPERSONIC DRAG 
OF FIN-STABILIZED PARABOLIC BODIES OF REV- 
OLUTION. H. Herbert Jackson. May 1952. 17p. 
diagrs., photos. (NACA RM L52B26) 



REDUCTION OF HELICOPTER PARASITE DRAG. 
Robert D. Harrington. August 1954. 8p. diagrs. 
(NACA TN 3234) 



AERODYNAMICS 
BODIES (1.3) 



53 



Protxiberances - Shape Variables 
(Cont. ) 



BOUNDARY-LAYER TRANSITION AT MACH 3.12 
WITH AND WITHOUT SINGLE ROUGHNESS 
ELEMENTS. Paul F. Brinich. December 1954. 
41 p. diagrs. (NACA TN 3267) 

EXPERIMENTS ON TURBULENT FLOW THROUGH 
CHANNELS HAVING POROUS ROUGH SURFACES 
WITH OR WITHOUT AIR INJECTION. E. R. G. 
Eckert, Anthony J. Diaguila and Patrick L. 
Donoughe. February 1955. 45p. diagrs., photos., 
tab. (NACA TN 3339) 

AN INVESTIGATION OF DRAINS DISCHARGING 
LIQUID INTO SUBSONIC AND TRANSONIC STREAMS. 
Allen R. Vick and Frank V. Silhan. March 1955. 
54p. diagrs., photos., tab. (NACA TN 3359) 



CANOPIES 
(1.3.3) 



WIND-TXraNEL INVESTIGATION AT A MACH NUM- 
BER OF 1.53 OF AN AIRPLANE WITH A TRIANGU- 
LAR WING. Richard Scherrer and William R. 
Wimbrow. January 23, 1948. 74p. diagrs., 
photos., 2 tabs. (NACA RM A7J05) 

STATIC STABILITY OF FUSELAGES HAVING A 
RELATIVELY FLAT CROSS SECTION. William R. 
Bates. March 1955. 29p. diagrs., tab. (NACA 
TN 3429. Formerly RM L9I06a) 



DUCTED BODIES 
(1.3.4) 



WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 1.53 OF AN AIRPLANE WITH A TRIANGU- 
LAR WING. Richard Scherrer and William R. 
Wimbrow. January 23, 1948. 74p. diagrs., 
photos., 2 tabs. (NACA RM A7J05) 

EXPERIMENTAL INVESTIGATION OF SUPERSONIC 
FLOW WITH DETACHED SHOCK WAVES FOR 
MACH NUMBERS BETWEEN 1.8 AND 2.9. W. E. 
Moeckel. July 5, 1950. 56p. diagrs., photos., 4 
tabs. (NACA RM E50D05) 

FUGHT DETERMINATION OF THE DRAG AND 
PRESSURE RECOVERY OF AN NACA 1-40-250 
NOSE INLET AT MACH NUMBERS FROM 0.9 TO 
1.8. R. I. Sears and C. F. Merlet. February 28, 
1951. 32p. diagrs., photos., 2 tabs. (NACA 
RM L50L18) 

AN INVESTIGATION OF SEVERAL NACA 1 -SERIES 
NOSE INLETS WITH AND WITHOUT PROTRUDING 
CENTRAL BODIES AT HIGH -SUBSONIC MACH 
NUMBERS AND AT A MACH NUMBER OF 1.2. 
Robert E. Pendley and Harold L. Robinson. May 
1955. 51p. diagrs., photos. (NACA TN 3436. 
Formerly RM L9L23a) 



NOSE SHAPE 
(1.3.4.1) 



AN INVESTIGATION OF THREE TRANSONIC FUSE- 
LAGE AIR INLETS AT MACH NUMBERS FROM 0.4 
TO 0.94 AND AT A MACH NUMBER OF 1.19. Robert 
E. Pendley, Harold L. Robinson and Claude V. 
WiUtams. November 7, 1950. 51p. diagrs., photos., 
3 tabs. (NACA RM L50H24) 

THE EXTERNAL-SHOCK DRAG OF SUPERSONIC 
INLETS HAVING SUBSONIC ENTRANCE FLOW. 
Louis M. Nucci. December 20, 1950. 28p. diagrs., 
photos. (NACA KM L50G14a) 

THE ORIGIN OF AERODYNAMIC INSTABILITY OF 
SUPERSONIC INLETS AT SUBCRITICAL CONDI- 
TIONS. Antonio Ferri and Louis M. Nucci. 
January 26, 1951. lllp. diagrs., photos., tab. 
(NACA RM L50K30) 

FUGHT DETERMINATION OF THE DRAG AND 
PRESSURE RECOVERY OF AN NACA 1-40-250 
NOSE INLET AT MACH NUMBERS FROM 0.9 TO 
1.8. R. I. Sears and C. F. Merlet. February 28, 
1951. 32p. diagrs., photos., 2 tabs. (NACA 
RM L50L18) 

LOW -SPEED INVESTIGATION OF THE EFFECTS OF 
ANGLE OF ATTACK ON THE PRESSURE RECOVERY 
OF A CIRCULAR NOSE INLET WITH SEVERAL LIP 
SHAPES. James R. Blackaby. May 1955. 30p. 
diagrs., photo. (NACA TN 3394) 



SIDE INLETS 
(1.3.4.3) 



PRESSURE RECOVERY AT SUPERSONIC SPEEDS 
THROUGH ANNULAR DUCT INLETS SITUATED IN 
A REGION OF APPRECIABLE BOUNDARY LAYER. 
I - ADDITION OF ENERGY TO THE BOUNDARY 
LAYER. Wallace F. Davis and George B. Brajnikoff. 
April 1, 1948. 22p. diagrs., photos. (NACA 
RM A8A13) 

AN EXPERIMENTAL INVESTIGATION OF NACA 
SUBMERGED INLETS AT HIGH SUBSONIC SPEEDS. 
I - INLETS FORWARD OF THE WING LEADING 
EDGE. Charles F. Hall and F. Dorn Barclay. 
June 9, 1948. 64p. diagrs., photos. (NACA 
RM A8B16) 

TANK SPRAY TESTS OF A JET-POWERED MODEL 
FITTED WITH NACA HYDRO-SKIS. Kenneth L. 
Wadlin and John A. Ramsen. July 22, 1948. 19p. 
diagrs., photos. (NACA RM L8B18) 

PRESSURE RECOVERY AT SUPERSONIC SPEEDS 
THROUGH ANNULAR DUCT INLETS SITUATED IN A 
REGION OF APPRECIABLE BOUNDARY LAYER, 
n - EFFECT OF AN OBUQUE SHOCK WAVE 
IMMEDIATELY AHEAD OF THE INLET. George B. 
Brajnlkoff. August 9, 1948. 15p. diagrs., photos. 
(NACA RM A8F08) 

RAM-RECOVERY CHARACTERISTICS OF NACA 
SUBMERGED INLETS AT HIGH SUBSONIC SPEEie. 
Charles F. Hall and Joseph L. Frank. November 17, 
1948. 4^. diagrs., photos. (NACA RM A8I29) 

THE EFFECT OF THE PROPELLER SLIPSTREAM 
ON THE CHARACTERISTICS OF SUBMERGED 
INLETS. Noel K. Delany. September 9, 1949. 
41p. diagrs., photos. (NACA RM A9G15) 



AERODYNAMICS 
54 BODIES (1.3) 



Side Inlets - Ducted Bodies (Cont. ) 



A COMPARISON OF TWO SUBMERGED INLETS AT 
SUBSONIC AND TRANSONIC-SPEEDS. Emmet A. 
Mossman. September 15, 1949. 31p. dlagrs., photos. 
(NACA RM A9F16) 

TESTS OF A SMALL-SCALE NACA SUBMERGED 
INLET AT TRANSONIC MACH NUMBERS. L. 
Stewart Rolls and George A. Rathert, Jr. 
February 23, 1950. 18p. diagrs., photos. (NACA 
RM A9L29) 

AN INVESTIGATION OF THREE TRANSONIC FUSE- 
LAGE AIR INLETS AT MACH NUMBERS FROM 0.4 
TO 0.94 AND AT A MACH NUMBER OF 1.19. Robert 
E. Pendley, Harold L. Robinson and Claude V. 
Williams. November 7, 1950. 51p. dlagrs., photos., 
3 tabs. (NACA RM L50H24) 

LOW -SPEED INVESTIGATION OF A SEMISUB- 
MERGED AIR SCOOP WITH AND WITHOUT 
BOUNDARY-LAYER SUCTION. P. Kenneth Plerpont 
and Robert R. Howell. February 23, 1951. 46p. 
diagrs., photos., 2 tabs. (NACA RM L50H15) 

AN EXPERIMENTAL INVESTIGATION AT SUBSONIC 
SPEEDS OF A SCOOP-TYPE AIR-INDUCTION 
SYSTEM FOR A SUPERSONIC AIRPLANE. Curt A. 
Holzhauser. July 1951. 45p. diagrs., photos. (NACA 
RM A51E24) 

COMPARISON OF DRAG, PRESSURE RECOVER\ 
AND SURFACE PRESSURE OF A SCOOP-TYPE IN- 
LET AND AN NACA SUBMERGED INLET AT TRAN- 
SONIC SPEEDS. Joseph L. Frank and Robert A. 
Taylor. December 1951. 63p. diagrs., photos. 
(NACA RM A51H20a) 

THE EFFECT OF ENTRANCE MACH NUMBER AND 
LIP SHAPE ON THE SUBSONIC CHARACTERISTICS 
OF A SCOOP-TYPE AIR-INDUCTION SYSTEM FOR 
A SUPERSONIC AIRPLANE. Curt A. Holzhauser. 
January 1952. 39p. diagrs., photos., tab. (NACA 
RM A51J19a) 

SOME EFFECTS OF SIDE-WALL MODIFICATIONS 
ON THE DRAG AND PRESSURE RECOVERY OF AN 
NACA SUBMERGED INLET AT TRANSONIC SPEEDS. 
Robert A. Taylor. February 1952. 25p. diagrs., 
photos. (NACA RM A51L03a. 



PRELIMINARY INVESTIGATION OF A SUBMERGED 
AIR SCOOP UTILIZING BOUNDARY-LAYER 
SUCTION TO OBTAIN INCREASED PRESSURE 
RECOVERY. Mark R. Nichols and P. Kenneth 
Pierpont. April 1955. 72p. diagrs., photos., 
2 tabs. (NACA TN 3437. Formerly RM L50A13) 



SIDE EXITS 
(1.3.4.4) 

A TRANSONIC INVESTIGATION OF THE AERO- 
DYNAMIC CHARACTERISTICS OF PLATE- AND 
BELL-TYPE OUTLETS FOR AUXH,IARY AIR. 
William J. Nelson and Paul E. Dewey. September 
1952. 25p. diagrs., photos. (NACA RM L52H20) 

A PRELIMINARY INVESTIGATION OF AERODYNA- 
MIC CHARACTERISTICS OF SMALL INCLINED AIR 
OUTLETS AT TRANSONIC MACH NUMBERS. 
Paul E. Dewey. May 1955. 21p. diagrs., photos. 
(NACA TN 3442. Formerly RM L53C10) 



HULLS 
(1.3.5) 



PRELIMINARY WIND-TUNNEL INVESTIGATION AT 
HIGH-SUBSONIC SPEEDS OF PLANING-TAIL, 
BLENDED, AND AIRFOIL-FOREBODY SWEPT 
HULLS. John M. Riebe and Richard G. MacLeod. 
September 12, 1949. 33p. diagrs., photos., 3 tabs. 
(NACA RM L9D01) 



AERODYNAMIC CHARACTERISTICS OF A REFINED 
DEEP-STEP PLANING-TAIL FLYING-BOAT HULL 
WITH VARIOUS FOREBODY AND AFTERBODY 
SHAPES. John M. Riebe and Rodger L. Naeseth. 
1953. il, 19p. diagrs., photos., 8 tabs. (NACA 
Rept. 1144. Formerly TN 2489; RM L8F01) 



AERODYNAMICS 56 



Internal Aerodynamics 
(1.4) 



EXPERIMENTAL INVESTIGATION OF TYPICAL 
CONSTANT- AND VARIABLE-AREA EXHAUST 
NOZZLES AND EFFECTS ON AXIAL-FLOW 
TURBOJET-ENGINE PERFORMANCE. Lewis E. 
Wallner and John T. Wintler. July 1951. 43p. 
diagrs., photos. (NACA RM E51D19) 

INVESTIGATION OF POWER EXTRACTION CHAR- 
ACTERISTICS AND BRAKING REQUIREMENTS OF A 
WINDMILLING TURBOJET ENGINE. Curtis L. 
Walker and David B. Fenn. July 1952. 31p. diagrs., 
tab. (NACA RM E52D30) 

INVESTIGATION TO DETERMINE EFFECTS OF 
RECTANGULAR VORTEX GENERATORS ON THE 
STATIC -PRESSURE DROP THROUGH A 90° CIRCU- 
LAR ELBOW. E. Floyd Valentine and Martin R. 
Copp. September 1953. 35p. diagrs., photos. 
(NACA RM L53G08) 

CONVECTION OF A PATTERN OF VORTICITY 
THROUGH A SHOCK WAVE. H. S. Ribner. 1954. 
ii, 17p. diagrs. (NACA Rept. 1164. Formerly 
TN 2864) 

UNSTEADY OBLIQUE INTERACTION OF A SHOCK 
WAVE WITH A PLANE DISTURBANCE. Franklin K. 
Moore. 1954. ii, 21p. diagrs. (NACA Rept. 1165. 
Formerly TN 2879) 

A NOTE ON SECONDARY FLOW IN ROTATING 
RADIAL CHANNELS. James J. Kramer and John 
D. Stanitz. 1954. ii, 12p. diagrs. (NACA 
Rept. 1179. Formerly TN 3013) 

REDUCTION OF HELICOPTER PARASITE DRAG. 
Robert D. Harrington. August 1954. 8p. diagrs. 
(NACA TN 3234) 

INVESTIGATION OF SHOCK DIFFUSERS AT MACH 
NUMBER 1.85. IH - MULTIPLE-SHOCK AND 
CURVED-CONTOUR PROJECTING CONES. W. E. 
Moeckel and J. F. Connors. August 13, 1947. 23p. 
diagrs., photos. (NACA RM E7F13) 



AIR INLETS 
(l.4.l) 



FLIGHT DETERMINATION OF THE DRAG AND 
PRESSURE RECOVERY OF AN NACA 1-40-250 
NOSE INLET AT MACH NUMBERS FROM 0.9 TO 
1.8. R. I. Sears and C. F. Merlet. February 28, 
1951. 32p. diagrs., photos., 2 tabs. (NACA 
RM L50L18) 

METHOD AND GRAPHS FOR THE EVALUATION OF 
AIR -INDUCTION SYSTEMS. George B. Brajnikotf. 
1953. ii, 22p. diagrs., tab. (NACA Rept. 1141. 
Formerly TN 2697) 

A METHOD FOR EVALUATING THE EFFECTS OF 
DRAG AND INLET PRESSURE RECOVERY ON 
PROPULSION-SYSTEM PERFORMANCE. Emil J. 
Kremzler. August 1954. 21p. diagrs. (NACA 
TN 3261) 

INGESTION OF FOREIGN OBJECTS INTO TURBINE 
ENGINES BY VORTICES. Lewis A. Rodert and 
Floyd B. Garrett. February 1955. 23p. diagrs., 
photos. (NACA TN 3330) 



NOSE, CENTRAL 
(1.4.1. 1) 

STUDY BY NACA WING-FLOW METHOD OF 
TRANSONIC DRAG CHARACTERISTICS OF A 
BLUNT-NOSE BODY OF REVOLUTION AND COM- 
PARISON WITH RESULTS FOR A SHARP -NOSE 
BODY. J. Ford Johnston and Mitchell Lopatoff, 
April 26, 1949. 26p. diagrs., photos. (NACA 
RM L9C11) 

SUPERSONIC TUNNEL INVESTIGATION BY MEANS 
OF INCLINED-PLATE TECHNIQUE TO DETERMINE 
PERFORMANCE OF SEVERAL NOSE INLETS OVER 
MACH NUMBER RANGE OF 1.72 TO 2.18. Jerome 
L. Fox. February 14, 1951. 27p. diagrs., photos. 
(NACA RM E50K14) 

PRESSURE DISTRIBUTION AT LOW SPEED ON A 
1/4-SCALE BELL X-5 AIRPLANE MODEL. 
William B. Kemp, Jr. and Albert G. Few, Jr. 
December 1951. 86p. diagrs., photos. (NACA 
RM L51I25) 

AMPLITUDE OF SUPERSONIC DIFFUSER FLOW 
PULSATIONS. William H. Sterbentz and Joseph 
Davids. December 1952. 23p. diagrs. (NACA 
RM E52I24) 



AN INVESTIGATION OF SEVERAL NACA 1-SERIES 
NOSE INLETS WITH AND WITHOUT PROTRUDING 
CENTRAL BODIES AT HIGH-SUBSONIC MACH 
NUMBERS AND AT A MACH NUMBER OF 1.2. 
Robert E. Pendley and Harold L. Robinson. May 
1955. 51p. diagrs., photos. (NACA TN 3436. 
Formerly RM L9L23a) 



Propeller -Spinner -Cowl 

Combinations 

(1.4. 1. 1. 1) 

SUBSONIC MACH AND REYNOLDS NUMBER 
EFFECTS ON THE SURFACE PRESSURES, GAP 
FLOW, PRESSURE RECOVERY, AND DRAG OF A 
NONROTATING NACA 1-SERIES E-TYPE COWLING 
AT AN ANGLE OF ATTACK OF 0°. Robert M. 
Reynolds and Robert I. Sammonds. July 1951. 73p. 
diagrs., photo., 3 tabs. (NACA RM A51E03) 



EFFECTS OF PROPELLER-SHANK GEOMETRY 
AND PROPELLER-SPINNER-JUNCTURE CONFIG- 
URATION ON CHARACTERISTICS OF AN NACA 1- 
SERIES COWLING-SPINNER COMBINATION WITH 
AN EIGHT-BLADE DUAL-ROTATION PROPELLER. 
Arvid L. Keith, Jr., Gene J. Bingham and Arnold J. 
Rubin. September 1951. 73p. diagrs., photos., 5 
tabs. (NACARM L51F26) 

EFFECTS OF PROPELLER-SPINNER JUNCTURE 
ON THE PRESSURE -RECOVERY CHARACTERIS- 
TICS OF AN NACA 1-SERIES D-TYPE COWL IN 
COMBINATION WITH A FOUR-BLADE SINGLE- 
ROTATION PROPELLER AT MACH NUMBERS UP 
TO 0.83 AND AT AN ANGLE OF ATTACK OF 0°. 
Robert I. Sammonds and Ashley J. Molk. June 1952. 
45p. diagrs., photos., tab. (NACA RM A52D01a) 



AERODYNAMICS 
56 INTERNAL (1.4) 



Propeller -Spinner -Cowl 
Combinations (Cont. ) 

EFFECTS OF COMPRESSIBILITY AT MACH NUM- 
BERS UP TO 0.8 ON INTERNAL-FLOW CHARAC- 
TERISTICS OF A COWLING-SPINNER COMBINA- 
TION EQUIPPED WITH AN EIGHT -BLADE DUAL- 
ROTATION PROPELLER. Gene J. Bingham and 
Arvid L. Keith, Jr. June 1953. 39p. diagrs., 
photos. (NACA RM L53E12) 

Subsonic 



(1.4. 1.1.2) 

SUBSONIC MACH AND REYNOLDS NUMBER 
EFFECTS ON THE SURFACE PRESSURES, GAP 
FLOW, PRESSURE RECOVERY, AND DRAG OF A 
NONROTATING NACA 1 -SERIES E-TYPE COWLING 
AT AN ANGLE OF ATTACK OF 0°. Robert M. 
Reynolds and Robert I. Sammonds. July 1951. 73p. 
diagrs., photo., 3 tabs. (NACA RM A5 1E03) 

EFFECTS OF PROPELLER-SHANK GEOMETRY 
AND PROPELLER -SPINNER -JUNCTURE CONFIG- 
URATION ON CHARACTERISTICS OF AN NACA 1- 
SEREES COWLING-SPINNER COMBINATION WITH 
AN EIGHT-BLADE DUAL-ROTATION PROPELLER. 
Arvid L. Keith, Jr., Gene J. Bingham and Arnold J. 
Rubin. September 1951. 73p. diagrs., photos., 5 
tabs. (NACARM L51F26) 

EFFECTS OF COMPRESSIBILITY AT MACH NUM- 
BERS UP TO 0.8 ON INTERNAL-FLOW CHARAC- 
TERISTICS OF A COWLING-SPINNER COMBINA- 
TION EQUIPPED WITH AN EIGHT -BLADE DUAL- 
ROTATION PROPELLER. Gene J. Bingham and 
Arvid L. Keith, Jr. June 1953. 39p. diagrs., 
photos. (NACA RM L53E12) 

LOW-SPEED INVESTIGATION OF THE EFFECTS OF 
ANGLE OF ATTACK ON THE PRESSURE RECOVERY 
OF A CIRCULAR NOSE INLET WITH SEVERAL LIP 
SHAPES. James R. Blackaby. May 1955. 30p. 
diagrs., photo. (NACA TN 3394) 



Supersonic 
(1.4.1.1.3) 



AN EXPERIMENTAL INVESTIGATION AT SUPER- 
SONIC SPEEDS OF ANNULAR DUCT INLETS 
SITUATED IN A REGION OF APPRECIABLE 
BOUNDARY LAYER. Wallace F. Davis, George B. 
Brajnikoft, Daviu L. Goldstein and Joseph M. 
Spiegel. September 24, 1947. 41p. diagrs., photos. 
(NACA RM A7G15) 

INVESTIGATION OF PERFORATED CONVERGENT- 
DIVERGENT DIFFUSERS WITH INITIAL BOUNDARY 
LAYER. Maynard L Weinstein. August 15, 1950. 
26p. diagrs., photo. (NACA RM E50F12) 

THE EXTERNAL-SHOCK DRAG OF SUPERSONIC 
INLETS HAVING SUBSONIC ENTRANCE FLOW. 
Louis M. Nucci. December 20, 1950. 28p. diagrs., 
photos. (NACA RM L50G14a) 

THE ORIGIN OF AERODYNAMIC INSTABILITY OF 
SUPERSONIC INLETS AT SUBCRITICAL CONDI- 
TIONS. Antonio Ferri and Louis M. Nucci. 
January 26, 1951. lllp. diagrs., photos., tab. 
(NACA RM L50K30) 

INVESTIGATION OF THREE TYPES OF SUPERSONIC 
DIFFUSER OVER A RANGE OF MACH NUMBERS 
FROM 1.75 TO 2.74. L. Eugene Baughman and 
Lawrence I. Gould. March 12, 1951. 37p. diagrs., 
photos. (NACA RM E50L08) 



AN ANALYSIS OF BUZZING IN SUPER^NIC BAM 
JETS BY A MODIFIED ONE -DIMENSIONAL NON- 
STATIONAHY WAVE THEORY. Robert L. Trimpi. 
March 1952. 72p. diagrs., photos. (NACA 
RM L52A18) 

A THEORY FOR STABILITY AND BUZZ PULSATION 
AMPLITUDE IN RAM JETS AMD AN EXPERIMEN- 
TAL INVESTIGATION INCLUDING SCALE EFFECTS. 
Robert L. Trimpi. October 1953. 75p. diagrs., 
photos., 3 tabs. (NACA RM L53G28) 

NOSE, ANNULAR 
(1.4.1.2) 

INVESTIGATION OF SHOCK DIFFUSERS AT MACH 
NUMBER 1.85. HI - MULTIPLE -SHOCK AND 
CURVED-CONTOUR PROJECTING CONES. W. E. 
Moeckel and J. F. Connors. August 13, 1947. 23p. 
diagrs., photos. (NACA RM E7F13) 

AN EXPERIMENTAL INVESTIGATION AT SUPER- 
SONIC SPEEDS OF ANNULAR DUCT INLETS 
SITUATED IN A REGION OF APPRECIABLE 
BOUNDARY LAYER. Wallace F. Davis, George B. 
BrajnikoH, David L. Goldstein and Joseph M. 
Spiegel. September 24, 1947. 41p. diagrs., photos. 
(NACA RM A7G15) 

AN INVESTIGATION OF THREE TRANSONIC FUSE- 
LAGE AIR INLETS AT MACH NUMBERS FROM 0.4 
TO 0.94 AND AT A MACH NUMBER OF 1.19. Robert 
E. Pendley, Harold L. Robinson and Claude V. 
Williams. November 7, 1950. 51p. diagrs., photos., 
3 tabs. (NACA RM L50H24) 

THE ORIGIN OF AERODYNAMIC INSTABILITY OF 
SUPERSONIC INLETS AT SUBCRITICAL CONDI- 
TIONS. Antonio Ferrl and Louis M. Nucci. 
January 26, 1951. lllp. diagrs., photos., tab. 
(NACA RM L50K30) 

SUPERSONIC TUNNEL INVESTIGATION BY MEANS 
OF INCLINED-PLATE TECHNIQUE TO DETERMINE 
PERFORMANCE OF SEVERAL NOSE INLETS OVER 
MACH NUMBER RANGE OF 1.72 TO 2.18. Jerome 
L. Fox. February 14, 1951. 27p. diagrs., photos. 
(NACA RM E50K14) 



AN ANALYSIS OF BUZZING IN SUPERSONIC RAM 
JETS BY A MODIFIED ONE -DIMENSIONAL NON- 
STATIONARY WAVE THEORY. Robert L. Trimpi. 
March 1952. 72p. diagrs., photos. (NACA 
RM L52A18) 

EFFECTS OF PROPELLER -SPINNER JUNCTURE 
ON THE PRESSURE -RECOVERY CHARACTERIS- 
TICS OF AN NACA 1 -SERIES D-TYPE COWL IN 
COMBINATION WITH A FOUR-BLADE SINGLE- 
ROTATION PROPELLER AT MACH NUMBERS UP 
TO 0.83 AND AT AN ANGLE OF ATTACK OF 0°. 
Robert I. Sammonds and Ashley J. Molk. June 1952. 
45p. diagrs., photos., tab. (NACA RM A52D01a) 



A THEORY FOR STABILITY AND BUZZ PULSATION 
AMPLITUDE IN RAM JETS AND AN EXPERIMEN- 
TAL INVESTIGATION INCLUDING SCALE EFFECTS. 
Robert L. Trimpi. October 1953. 75p. diagrs., 
photos., 3 tabs. (NACA RM LS3G28) 

AN INVESTIGATION OF SEVERAL NACA 1 -SERIES 
NOSE INLETS WITH AND WITHOUT PRQTRUDING 
CENTRAL BODIES AT HIGH-SUBSONIC MACH 
NUMBERS AND AT A MACH NUMBER OF 1.2. 
Robert E. Pendley and Harold L. Robinson. May 
1955. 51p. diagrs., photos. (NACA TN 3436. 
Formerly RM L9L23a) 



AERODYNAMICS 
INTERNAL (1,4) 



57 



WING LEADING EDGE 
(1.4.1.3) 

LOW -SPEED WIND-TUNNEL INVESTIGATION OF A 
TRIANGULAR SWEPTBACK AIR INLET IN THE 
ROOT OF A 45° SWEPTBACK WING. Arvid L. 
Keith, Jr. and Jack Schiff. January 1955. 65p. 
diagrs., photos., 5 tabs. (NACA TN 3363. Formerly 
RM L50I01) 

SIDE 
(1.4.1.4) 

AN INVESTIGATION OF THREE TRANSONIC FUSE- 
LAGE AIR INLETS AT MACH NUMBERS FROM 0.4 
TO 0.94 AND AT A MACH NUMBER OF 1.19. Robert 
E. Pendley, Harold L. Robinson and Claude V. 
Williams. November 7, 1950. 51p. diagrs., photos., 
3 tabs. (NACA RM L50H24) 

INVESTIGATION OF AN NACA SUBMERGED INLET 
AT MACH NUMBERS FROM 1.17 to 1.99. Warren 
E. Anderson and Alson C. Frazer. September 1952. 
29p. diagrs., photo. (NACA RM A52F17) 

LOW-SPEED WIND-TUNNEL INVESTIGATION OF A 
TRIANGULAR SWEPTBACK AIR INLET IN THE 
ROOT OF A 45° SWEPTBACK WING. Arvid L. 
Keith, Jr. and Jack Schiff. January 1955. 65p. 
diagrs., photos., 5 tabs. (NACA TN 3363. Formerly 
RM L50I01) 

Scoops 
(1.4.1.4.1) 

PRESSURE RECOVERY AT SUPERSONIC SPEEDS 
THROUGH ANNULAR DUCT INLETS SITUATED IN 
A REGION OF APPRECIABLE BOUNDARY LAYER. 
I - ADDITION OF ENERGY TO THE BOUNDARY 
LAYER. Wallace F. Davis and George B. Brajnikoff. 
April 1, 1948. 22p. diagrs., photos. (NACA 
RM A8A13) 

PRESSURE RECOVERY AT SUPERSONIC SPEEDS 
THROUGH ANNULAR DUCT INLETS SITUATED IN A 
REGION OF APPRECIABLE BOUNDARY LAYER, 
n - EFFECT OF AN OBLIQUE SHOCK WAVE 
IMMEDIATELY AHEAD OF THE INLET. George B. 
BrajnUcoft. August 9, 1948. 15p. diagrs., photos. 
(NACA RM A8F08) 

LOW-SPEED INVESTIGATION OF A SEMISUB- 
MERGED AIR SCOOP WITH AND WITHOUT 
BOUNDARY-LAYER SUCTION. P. Kenneth Pierpont 
and Robert R. Howell. February 23, 1951. 46p. 
diagrs., photos., 2 tabs. (NACA RM L50H15) 

AN EXPERIMENTAL INVESTIGATION AT SUBSONIC 
SPEEDS OF A SCOOP-TYPE AIR-INDUCTION 
SYSTEM FOR A SUPERSONIC AIRPLANE. Curt A. 
Holzhauser. July 1951. 45p. diagrs., photos. (NACA 
RM A51E24) 

COMPARISON OF DRAG, PRESSURE RECOVERS 
AND SURFACE PRESSURE OF A SCOOP-TYPE IN- 
LET AND AN NACA SUBMERGED INLET AT TRAN- 
SONIC SPEEDS. Joseph L. Frank and Robert A. 
Taylor. December 1951. 63p. diagrs., photos. 
(NACA RM A51H20a) 

THE EFFECT OF ENTRANCE MACH NUMBER AND 
LIP SHAPE ON THE SUBSONIC CHARACTERISTICS 
OF A SCOOP-TYPE AIR-INDUCTION SYSTEM FOR 
A SUPERSONIC AIRPLANE. Curt A. Holzhauser. 
January 1952. 39p. diagrs., photos., tab. (NACA 
RM A51J19a) 



PRELIMINARY INVESTIGATION OF A SUBMERGED 
AIR SCOOP UTILIZING BOUNDARY-LAYER 
SUCTION TO OBTAIN INCREASED PRESSURE 
RECOVERY. Mark R. Nichols and P. Kenneth 
Pierpont. April 1955. 72p. diagrs., photos., 
2 tabs. (NACA TN 3437. Formerly RM L50A13) 

Submerged 
(1.4.1.4.2) 

AK EXPERIMENTAL INVESTIGATION OF NACA 
SUBMERGED INLETS AT HIGH SUBSONIC SPEEDS. 

1 - INLETS FORWARD OF THE WING LEADING 
EDGE. Charles P. Hall and F. Dorn Barclay. 
June 9, 1948. 64p. diagrs., photos. (NACA 
RM A8B16) 

AN EXPERIMENTAL INVESTIGATION AT LARGE 
SCALE OF SEVERAL CONFIGURATIONS OF AN 
NACA SUBMERGED AIR INTAKE. Norman J. 
Martin and Curt A. Holzhauser. October 19, 1948. 
68p. diagrs., photos., 7 tabs. (NACA RM A8F21) 

RAM-RECOVERY CHARACTERISTICS OF NACA 
SUBMERGED INLETS AT HIGH SUBSONIC SPEEDS. 
Charles F. Hall and Joseph L. Frank. November 17, 

1948. 4^. di^rs., photos. (NACA RM A8I29) 

AN EXPERIMENTAL INVESTIGATION AT LARGE 
SCALE OF SINGLE AND TWIN NACA SUBMERGED 
SIDE INTAKES AT SEVERAL ANGLES OF SIDESLIP. 
Norman J. Martin and Curt A. Holzhauser. August 1, 

1949. 31p. diagrs., photo. (NACA RM A9F20) 

THE EFFECT OF THE PROPELLER SLIPSTREAM 
ON THE CHARACTERISTICS OF SUBMERGED 
INLETS. Noel K. Delany. September 9, 1949. 
41p. diagrs., photos. (NACA RM A9G15) 

A COMPARISON OF TWO SUBMERGED INLETS AT 
SUBSONIC AND TRANSONICSPEEDS. Emmet A. 
Mossman. September 15, 1949. 31p. diagrs., photos. 
(NACA RM A9F16) 

TESTS OF A SMALL-SCALE NACA SUBMERGED 
INLET AT TRANSONIC MACH NUMBERS. L. 
Stewart Rolls and George A. Rathert, Jr. 
February 23, 1950. 18p. diagrs., photos. (NACA 
RM A9L29) 

PRELIMINARY INVESTIGATION OF THE TRAN- 
SONIC CHARACTERISTICS OF AN NACA SUB- 
MERGED INLET. John A. Axelson and Robert A. 
Taylor. June 5, 1950. 44p. diagrs., photos. 
(NACA RM A50C13) 

LOW -SPEED INVESTIGATION OF A SEMISUB- 
MERGED AIR SCOOP WITH AND WITHOUT 
BOUNDARY-LAYER SUCTION. P. Kenneth Pierpont 
and Robert R. Howell. February 23, 1951. 45p. 
diagrs., photos., 2 tabs. (NACA RM L50H15) 

COMPARISON OF DRAG, PRESSURE RECOVERY 
AND SURFACE PRESSURE OF A SCOOP-TYPE IN- 
LET AND AN NACA SUBMERGED INLET AT TRAN- 
SONIC SPEEDS. Joseph L. Frank and Robert A. 
Taylor. December 1951. 63p. diagrs., photos. 
(NACA RM A51H20a) 

SOME EFFECTS OF SIDE -WALL MODIFICATIONS 
ON THE DRAG AND PRESSURE RECOVERY OF AN 
NACA SUBMERGED INLET AT TRANSONIC SPEEDS. 
Robert A. Taylor. February 1952. 25p. diagrs., 
photos. (NACA RM A51L03a. 

PRELIMINARY INVESTIGATION OF A SUBMERGED 
AIR SCOOP UTILIZING BOUNDARY-LAYER 
SUCTION TO OBTAIN INCREASED PRESSURE 
RECOVERY. Mark R. Nichols and P. Kenneth 
Pierpont. April 1955. 72p. diagrs., photos., 

2 tabs. (NACA TN 3437. Formerly RM L50A13) 



AERODYNAMICS 
58 INTERNAL (1.4) 



Submerged - Air Inlets (Cont. ) 

INVESTIGATION OF AN NACA SUBMERGED INLET 
AT MACH NUMBERS FROM 1.17 to 1.99. Warren 
E. Anderson and Alson C. Frazer. September 1952. 
29p. diagrs., photo. (NACA RM A52F17) 



DUCTS 
(1.4.2) 



INVESTIGATION TO DETERMINE EFFECTS OF 
RECTANGULAR VORTEX GENERATORS ON THE 
STATIC -PRESSURE DROP THROUGH A 90° CIRCU- 
LAR ELBOW. E. Floyd Valentine and Martin R. 
Copp. September 1953. 35p. diagrs., photos. 
(NACA RM LS3G08) 

TRANSVERSE OSCILLATIONS IN A CYLINDRICAL 
COMBUSTION CHAMBER. Franklin K. Moore and 
Stephen H. Maslen. October 1954. 25p. diagrs. 
(NACA TN 3152) 

ANALYSIS OF LAMINAR FORCED-CONVECTION 
HEAT TRANSFER IN ENTRANCE REGION OF FLAT 
RECTANGULAR DUCTS. E. M. Sparrow. January 
1955. 42p. diagrs. (NACA TN 3331) 

ANALYSIS OF ERRORS INTRODUCED BY SEVERAL 
METHODS OF WEIGHTING NONUNIFORM DUCT 
FLOWS. DeMarquis D. Wyatt. March 1955. 40p. 
diagrs. (NACA TN 3400) 

DIFFUSERS 
(1.4.2.1) 

FLIGHT TESTS OF A TWO-DIMENSIONAL WEDGE 
DIFFjUSER AT TRANSONIC AND SUPERSONIC 
SPEEDS. M. A. Faget. August 11, 1948. 21p. 
diagrs., photos. (NACA RM L8E27) 

FLIGHT DETERMINATION OF THE DRXG AND 
PRESSURE RECOVERY OF AN NACA 1-40-250 
NOSE INLET AT MACH NUMBERS FROM 0.9 TO 
1.8. R. I. Sears and C. F. Merlet. February 28, 
1951. 32p. diagrs., photos., 2 tabs. (NACA 
RM L50L18) 

EFFECTS OF SOME PRIMARY VARIABLES OF 
RECTANGULAR VORTEX GENERATORS ON THE 
STATIC -PRESSURE RISE THROUGH A SHORT. 
DIFFUSER. E. Floyd Valentine and Raymond B. 
Carroll. May 1952. 32p. diagrs., photo., tab. 
(NACA RM L52B13) 

STARTING AND OPERATING LIMITS OF TWO 
SUPERSONIC WIND TUNNELS UTILIZING AUXIL- 
IARY AIR INJECTION DOWNSTREAM OF THE 
TEST SECTION. Henry R. Hunczak and Morris D. 
Rousso. September 1954. 28p. diagrs., photo. 
(NACA TN 3262) 

Subsonic 



(1.4.2.1.1) 

EFFECTS OF SEVERAL ARRANGEMENTS OF REC- 
TANGULAR VORTEX GENERATORS ON THE 
STATIC-PRESSURE RISE THROUGH A SHORT 2:1 
DIFFUSER. E. Floyd Valentine and Raymond B. 
Carroll. February 20, 1951. 35p. diagrs., photos. 
(NACA RM L50L04) 

PRELIMINARY INVESTIGATION OF THE EFFECTS 
OF RECTANGULAR VORTEX GENERATORS ON 
THE PERFORMANCE OF A SHORT 1.9:1 
STRAIGHT -WALL ANNULAR DIFFUSER. Charles 
C. Wood. October 1951. 27p. diagrs., photo., tab. 
(NACA RM L51G09) 



EFFECTS OF SOME PRIMARY VARIABLES OF 
RECTANGULAR VORTEX GENERATORS ON THE 
STATIC-PRESSURE RBE THROUGH A SHORT 
DIFFUSER. E. Floyd Valentine and Raymond B. 
Carroll. May 1952. 32p. diagrs., photo., tab. 
(NACA RM L52B13) 

EFFECTS OF COMPRESSIBILITY AT MACH NUM- 
BERS UP TO 0.8 ON INTERNAL-FLOW CHARAC- 
TERISTICS OF A COWLING-SPINNER COMBINA- 
TION EQUIPPED WITH AN EKHIT-BLADE DUAL- 
ROTATION PROPELLER. Gene J. Bingham and 
Arvid L. Keith, Jr. June 1953. 39p. diagrs., 
photos. (NACA RM L53E12) 

ANALYSIS OF ERRORS INTRODUCED BY SEVERAL 
METHODS OF WEIGHTING NONinOFORM DUCT 
FLOWS. DeMarquis D. Wyatt. March 1955. 40p. 
diagrs. (NACA TN 3400) 

LOW-SPEED INVESTIGATION OF THE EFFECTS OF 
ANGLE OF ATTACK ON THE PRESSURE RECOVERY 
OF A CIRCULAR NOSE INLET WITH SEVERAL LIP 
SHAPES. James R. Blackaby. May 1955. 30p. 
diagrs., photo. (NACA TN 3394) 



Supersonic 
(1.4.2.1.2) 



INVESTIGATION OF SHOCK DIFFUSERS AT MACH 
NUMBER 1.85. IH - MULTIPLE-SHOCK AND 
CURVED-CONTOUR PROJECTING CONES. W. E. 
Moeckel and J. F. Connors. August 13, 1947. 23p. 
diagrs., photos. (NACA RM E7F13) 

INVESTIGATION OF PERFORATED CONVERGENT- 
DIVERGENT DIFFUSERS WITH INITIAL BOUNDARY 
LAYER. Maynard I. Weinstein. August 15, 1950. 
26p. diagrs., photo. (NACA RM E50F12) 

THE EXTERNAL-SHOCK DRAG OF SUPERSONIC 
INLETS HAVING SUBSONIC ENTRANCE FLOW. 
Louis M. Nucci. December 20, 1950. 28p. diagrs., 
photos. (NACA RM L50G14a) 

THE ORIGIN OF AERODYNAMIC INSTABILITY OF 
SUPERSONIC INLETS AT SUBCRITICAL CONDI- 
TIONS. Antonio Ferri and Louis M. Nucci. 
January 26, 1951. lllp. diagrs., photos., tab. 
(NACA RM L50K30) 

INVESTIGATION OF THREE TYPES OF SUPERSONIC 
DIFFUSER OVER A RANGE OF MACH NUMBERS 
FROM 1.T5 TO 2.74. L. Eugene Baughman and 
Lawrence I. Gould. March 12, 1951. 37p. diagrs., 
photos. (NACA RM E50L08) 

CRITERIONS FOR PREDICTION AND CONTROL OF 
RAH-JET FLOW PULSATIONS. William H. 
Sterbentz and John C. Eward. May 16, 1951. 63p. 
diagrs., photos. (NACA RH E51C27) 

AN ANALYSIS OF BUZZING IN SUPERSONIC RAM 
JETS BY A MODIFIED ONE -DIMENSIONAL NON- 
STATIONARY WAVE THEORY. Robert L. Trimpi. 
March 1952. 72p. diagrs., photos. (NACA 
RM L52A18) 

AMPLITUDE OF SUPERSONIC DIFFISER FLOW 
PULSATIONS. William H. Sterbentz and Joseph 
Davids. December 1952. 23p. diagrs. (NACA 
RM E52I24) 

METHOD AND GRAPHS FOR THE EVALUATION OF 
AIR -INDUCTION SYSTEMS. George B. Brajnikoff. 
1953. ii, 22p. diagrs., tab. (NACA Rept. 1141. 
Formerly TN 2697) 

A THEORY FOR STABILITY AND BUZZ PULSATION 
AMPLITUDE IN RAM JETS AND AN EXPERIMEN- 
TAL INVESTIGATION INCLUDING SCALE EFFECTS. 
Robert L. Trimpi. October 1953. 75p. diagrs., 
photos., 3 tabs. (NACA RM L53G28) 



AERODYNAMICS 
INTERNAL (1.4) 59 



Supersonic - Ducts (Cont.^ 

A METHOD FOR EVALUATING THE EFFECTS OF 
DRAG AND INLET PRESSURE RECOVERY ON 
PROPULSION-SYSTEM PERFORMANCE. Emll J. 
Kremzier. August 1954. 21p. diagrs. (NACA 
TN 3261) 

SHOCKS IN HELICAL FLOWS THROUGH ANNULAR 
CASCADES OF STATOR BLADES. Robert 
Wasserman and Arthur W. Goldstein. December 
1954. 27p. diagrs. (NACA TN 3329) 

EFFECT OF A DISCONTINUITY ON TURBULENT 
BOUNDARY-LAYER-THICKNESS PARAMETERS 
WITH APPLICATION TO SHOCK-INDUCED SEPARA- 
TION. Eli Reshotko and Maurice Tucker. May 1955. 
21p. diagrs. (NACA TN 3454) 

NOZZLES 
(1.4.2.2) 

AN 8-FOOT AXISYMMETRICAL FIXED NOZZLE 
FOR SUBSONIC MACH NUMBERS UP TO 0.99 AND 
FOR A SUPERSONIC MACH NUMBER OF 1.2. 
Virgil S. Ritchie, Ray H. Wright and Marshall P. 
Tulin. February 23, 1950. 52p. diagrs., photos., 
2 tabs. (NACA RM L50A03a) 

EXPERIMENTAL INVESTIGATION OF TYPICAL 
CONSTANT- AND VARIABLE-AREA EXHAUST 
NOZZLES AND EFFECTS ON AXIAL-FLOW 
TURBOJET -ENGINE PERFORMANCE. Lewis E. 
Wallner and John T. Wintler. July 1951. 43p. 
diagrs., photos. (NACA RM E51D19) 

APPARATUS FOR OBTAINING A SUPERSONIC 
FLOW OF VERY SHORT DURATION AND SOME 
DRAG MEASUREMENTS OBTAINED WITH ITS USE. 
John E. Yeates, Jr. , F. J. Bailey, Jr. and T. J. 
Voglewede. July 23, 1951. 23p. diagrs , photos. 
(NACA RM L9C01) 

AN ACCURATE AND RAPID METHOD FOR THE 
DESJCarOF SUPERSONIC NOZZLES. Ivan E. 
Beckwith and John A. Moore. February 1955. 
57p. diagrs., 3 tabs. (NACA TN 3322) 

PIPES 
(1.4.2.3) 

AERODYNAMIC LOSSES IN LOW-PRESSURE TAIL- 
PIPE EXHAUST DUCTS FOR ROCKET-PROPELLED 
AIRCRAFT. W. K. Hagginbothom and J. G. 
Thibodaux. July 20, 1948. 15p. diagrs., photos. 
(NACA RM L8C25) 

EXPERIMENTAL EVALUATION OF MOMENTUM 
TERMS IN TURBULENT PIPE FLOW. Virgil A. 
Sandborn. January 1955. 40p. diagrs. (NACA 
TN 3266) 

ANALYSIS OF ERRORS INTRODUCED BY SEVERAL 
METHODS OF WEIGHTING NONUNIFORM DUCT 
FLOWS. DeMarquis D. Wyatt. March 1955. 40p. 
diagrs. (NACA TN 3400) 

ANALYSIS OF FULLY DEVELOPED TURBULENT 
HEAT TRANSFER AND FLOW IN AN ANNULUS 
WITH VARIOUS ECCENTRICITIES. Robert G. 
Deissler and Maynard F. Taylor. May 1955. 42p. 
diagrs. (NACA TN 3451) 



BENDS 
(1.4.2.4) 

INVESTIGATION TO DETERMINE EFFECTS OF 
RECTANGULAR VCRTEX GENERATORS ON THE 
STATIC -PRESSURE DROP THROUGH A 90° CIRCU- 
LAR ELBOW. E. Floyd Valentine and Martin R. 
Copp. September 1953. 35p. diagrs., photos. 
(NACA RM L53G08) 



EXITS 
(1.4.3) 



A TRANSONIC INVESTIGATION OF THE AERO- 
DYNAMIC CHAHACTERBTICS OF PLATE- AND 
BELL-TYPE OUTLETS FOR AUXILIARY AIR. 
William J. Nelson and Paul E. Dewey. September 
1952. 25p. diagrs., photos. (NACA RM L52H20) 

FLIGHT MEASUREMENTS OF BASE PRESSURE ON 
BODIES OF REVOLUTION WITH AND WITHOUT 
SIMULATED ROCKET CHAMBERS. Robert F. Peck. 
April 1955. I8p. diagrs., photo. (NACA TN 3372. 
Formerly RM L50I28a) 



A PRELIMINARY INVESTIGATION OF AERODYNA- 
MIC CHARACTERISTICS OF SMALL INCLINED AIR 
OUTLETS AT TRANSONIC MACH NUMBERS. 
Paul E. Dewey. May 1955. 21p. diagrs., photos. 
(NACA TN 3442. Formerly RM L53C10) 

INVESTIGATION OF JET-ENGINE NOISE REDUC- 
TION BY SCREENS LOCATED TRANSVERSELY 
ACROSS THE JET. Edmund E. Callaghan and 
Willard D. Coles. May 1955. 27p. diagrs., photos., 
tab. (NACA TN 3452) 



JET PUMPS AND THRUST 
AU6MENTORS 

(1.4.4) 



EXPERIMENTAL INVESTIGATION OF TYPICAL 
CONSTANT- AND VARIABLE-AREA EXHAUST 
NOZZLES AND EFFECTS ON AXIAL-FLOW 
TURBOJET -ENCaNE PERFORMANCE. Lewis E. 
Wallner and John T. Wintler. July 1951. 43p. 
diagrs., photos. (NACA RM E51D19) 

WING-FLOW STUDY OF PRESSURE-DRAG REDUC- 
TION AT TRANSONIC SPEED BY PROJECTING A 
JET OF AIR FROM THE NOSE OF A PROLATE 
SPHEROID OF FINENESS RATIO 6. Mitchell 
Lopatoff. October 1951. 20p. photos., diagrs., tab. 
(NACA RM L51E09) 



THEORY OF THE JET SYPHON. B. Szczeniowski, 
University of Montreal. May 1955. 49p. diagrs., 
3 tabs. (NACA TN 3385) 



AERODYNAMICS 
60 INTERNAL (1.4) 



CASCADiS 
(1.4.5) 



ICING CHAHACTERISTICS AND ANTI-ICING HEAT 
REQUIREMENTS FOR HOLLOW AND INTERNALLY 
MODIFIED GAS-HEATED INLET GUIDE VANES. 
Vernon H. Gray and Dean T. Bowden. December 5, 
1950. 49p. diagrs., photos. (NACA RM E50I08) 

A VISUALIZATION STUDY OF SECONDARY FLOWS 
IN CASCADES. Howard Z. Herzig, Arthur G. 
Hansen and George R. Costello. 1954. ii, 51p. 
diagrs., photos. (NACA Rept. 1163. Formerly 
TN 2947; HM E52F19) 

THEORY 
(1.4.5. 1) 

LIFT AND MOMENT EQUATIONS FOR OSCILLAT- 
ING AIRFOILS IN AN INFINITE UNSTAGGERED 
CASCADE. Alexander Mendelson and Robert W. 
Carroll. October 1954. 46p. diagrs., 3 tabs. 
(NACA TN 3263) 

APPROXIMATE EFFECT OF LEADING-EDGE 
THICKNESS, INCIDENCE ANGLE, AND INLET 
MACH NUMBER ON INLET LOSSES FOR HIGH- 
SOLIDITY CASCADES OF LOW CAMBERED 
BLADES. Linwood C. Wright. December 1954. 
38p. diagrs. (NACA TN 3327) 

SHOCKS IN HELICAL FLOWS THROUGH ANNULAR 
CASCADES OF STATOR BLADES. Robert 
Wasserman and Arthur W. Goldstein. December 
1954. 27p. diagrs. (NACA TN 3329) 

EXPERIMENT 
(1.4.5.2) 

PREDICTION OF LOSSES INDUCED BY ANGLES OF 
ATTACK IN CASCADES OF SHARP-NOSED BLADES 
FOR INCOMPRESSIBLE AND SUBSONIC COMPRES- 
SIBLE FLOW. James J. Kramer and John D. 
Stanitz. January 1955. 45p. diagrs. (NACA 
TN 3149) 

INVESTIGATION OF POWER REQUIREMENTS FOR 
ICE PREVENTION AND CYCLICAL DE-ICING OF 
INLET GUIDE VANES WITH INTERNAL ELECTRIC 
HEATERS. Uwe von Glahn and Robert E. Blatz. 
December 1, 1950. 49p. diagrs., photos. (NACA 
RM E50H29) 

SECONDARY FLOWS AND BOUNDARY-LAYER 
ACCUMULATIONS IN TURBINE NOZZLES. Harold 
E. Rohlik, Milton G. Kofskey, Hubert W. Allen and 
Howard Z. Herzig. 1954. ii, 32p. diagrs., photos., 
3 tabs. (NACA Rept. 1168. Formerly TN 2871; 
TN 2909; TN 2989) 

SMOKE STUDY OF NOZZLE SECONDARY FLOWS 
IN A LOW-SPEED TURBINE. Milton G. Kofskey 
and Hubert W. Allen. November 1954. 24p. diagrs. , 
photos. (NACA TN 3260) 

APPROXIMATE EFFECT OF LEADING-EDGE 
THICKNESS, INCIDENCE ANGLE, AND INLET 
MACH NUMBER ON INLET LOSSES FOR HIGH- 
SOLIDITY CASCADES OF LOW CAMBERED 
BLADES. Linwood C. Wright. December 1954. 
38p. diagrs. (NACA TN 3327) 



BOUNDARY LAYER 
(1.4.7) 

AN EXPERIMENTAL INVESTIGATION AT SUPER- 
SONIC SPEEDS OF ANNULAR DUCT INLETS 
SITUATED IN A REGION OF APPRECIABLE 
BOUNDARY LAYER. Wallace F. Davis, George B. 
Brajnikoff, Davia L. Goldstein and Joseph M. 
Spiegel. September 24, 1947. 41p. diagrs., photos. 
(NACA RM A7G15) 

STUDY OF THE MOMENTUM DISTRIBUTION OF 
TURBULENT BOUNDARY LAYERS IN ADVERSE 
PRESSURE GRADIENTS. Virgil A. Sandborn and 
Raymond J. Slogar. January 1955. 79p. diagrs., 
photos. (NACA TN 3264) 

ANALYSIS OF LAMINAR FORCED-CONVECTION 
HEAT TRANSFER IN ENTRANCE REGION OF FLAT 
RECTANGULAR DUCTS. E. M. Sparrow. .Taiuiary 
1955. 42p. diagrs. (NACA TN 3331) 

LOW -SPEED WIND-TUNNEL INVESTIGATION OF A 
TRIANGULAR SWEPTBACK AIR INLET IN THE 
ROOT OF A 45° SWEPTBACK WING. Arvid L. 
Keith, Jr. and Jack Schiff. January 1955. 65p. 
diagrs., photos., 5 tabs. (NACA TN 3363. Formerly 
RM L50I01) 

SIMILAR SOLUTIONS FOR THE COMPRESSIBLE 
LAMINAR BOUNDARY LAYER WITH HEAT 
TRANSFER AND PRESSURE GRADIENT. Clarence 
B. Cohen and Eli Reshotko. February 1955. 67p. 
diagrs., 2 tabs. (NACA TN 3325) 

A THEORY FOR PREDICTING THE FLOW OF REAL 
GASES IN SHOCK TUBES WITH EXPERIMENTAL 
VERIFICATION. Robert L. Trimpi and Nathaniel B. 
Cohen. March 1955. 69p. diagrs., photo. 
(NACA TN 3375) 

LAMINAR BOUNDARY LAYER BEHIND SHOCK 
ADVANCING INTO STATIONARY FLUID. Harold 
Mirels. March 1955. 25p. diagrs., 2 tabs. (NACA 
TN 3401) 



THE COMPRESSIBLE LAMINAR BOUNDARY LA YER 
WITH HEAT TRANSFER AND ARBITRARY PRES- 
SURE GRADIENT. Clarence B. Cohen and Eli 
Reshotko. April 1955. 43p. diagrs., 2 tabs. (NACA 
TN 3326) 

LONGITUDINAL TURBULENT SPECTRUM SURVEY 
OF BOUNDARY LAYERS IN ADVERSE PRESSURE 
GRADIENTS. Virgil A. Sandborn and Raymond J. 
Slogar. May 1955. 40p. diagrs., tab. (NACA 
TN 3453) 



CHARACTERISTICS 
(1,4.7.1) 



A VISUALIZATION STUDY OF SECONDARY FLOWS 
IN CASCADES. Howard Z. Herzig, Arthur G. 
Hansen and George R. Costello. 1954. ii, 51p. 
diagrs., photos. (NACA Rept. 1163. formerly 
TN 2947; RM E52F19) 



AERODYNAMICS 
INTERNAL (1.4) 61 



Characteristics 
(Cont. ) 



Boundary Layer 



SECONDARY FLOWS AND BOUNDARY-LAYER 
ACCUMULATIONS IN TURBINE NOZZLES. Harold 
E. Rohlik, Milton G. Kofskey, Hubert W. Allen and 
Howard Z. Herzlg. 1954. il, 32p. diagrs., photos., 
3 tabs. (NACA Rept. 1168. Formerly TN 2871; 
TN 2909; TN 2989) 



SMOKE STUDY OF NOZZLE SECONDARY FLOWS 
IN A LOW-SPEED TURBINE. Milton G. Kofskey 
and Hubert W. AUen. November 1954. 24p. diagrs. 
photos. (NACA TN 3260) 



EXPERIMENTAL EVALUATION OF MOMENTUM 
TERMS IN TURBULENT PIPE FLOW. Virgil A. 
Sandborn. January 1955. 40p. diagrs. (NACA 
TN 3266) 



CONTROL 
(1.4:7.2) 



EFFECTS OF SEVERAL ARRANGEMENTS OF REC- 
TANGULAR VORTEX GENERATORS ON THE 
STATIC-PRESSURE RISE THROUGH A SHORT 2:1 
DIFFUSER. E. Floyd Valentine and Raymond B. 
Carroll. February 20, 1951. 35p. diagrs., photos. 
(NACA RM L50L04) 

LOW -SPEED INVESTIGATION OF A SEMISUB- 
MERGED AIR SCOOP WITH AND WITHOUT 
BOUNDARY-LAYER SUCTION. P. Kenneth Pierpont 
and Robert R. Howell. February 23, 1951. 46p. 
diagrs., photos., 2 tabs. (NACA RM L50H15) 



EFFECTS OF PROPELLER -SHANK GEOMETRY 
AM> PROPELLER-SPINNER-JUNCTURE CONFIG- 
URATION ON CHARACTERBTICS OF AN NACA 1- 
SERIES COWLING-SPINNER COMBINATION WITH 
AN EIGHT-BLADE DUAL-ROTATION PROPELLER. 
Arvid L. Keith, Jr., Gene J. Bingham and Arnold J. 
Rubin. September 1951. 73p. diagrs., photos., 5 
tabs. (NACA RM L51F26) 

PRELIMINARY INVESTIGATION OF THE EFFECTS 
OF RECTANGULAR VORTEX GENERATORS ON 
THE PERFORMANCE OF A SHORT 1.9:1 
STRAIGHT -WALL ANNULAR DIFFUSER. Charles 
C. Wood. October 1951. 27p. diagrs., photo., tab. 
(NACA RM L51G09) 

EFFECTS OF SOME PRIMARY VARIABLES OF 
RECTANGULAR VORTEX GENERATORS ON THE 
STATIC -PRESSURE RISE THROUGH A SHORT 
DIFFUSER. E. .Floyd Valentine and Raymond B. 
Carroll. May 1952. 32p. diagrs., photo., tab. 
(NACA RM L52B13) 

INVESTIGATION TO DETERMINE EFFECTS OF 
RECTANGULAR VORTEX GENERATORS ON THE 
STATIC -PRESSURE DROP THROUGH A 90° CIRCU- 
LAR ELBOW. E. Floyd Valentine and Martin R. 
Copp. September 1953. 35p. diagrs., photos. 
(NACA RM L53G08) 

A FIBROUS-GLASS COMPACT AS A PERMEABLE 
MATERIAL FOR BOUNDARY -LAYER-CONTROL 
APPLICATIONS USING AREA SUCTION. Robert E. 
Dannenberg, James A. Weiberg and Bruno J. 
Gambucci. January 1955. 20p. diagrs., photos., 
2 tabs. (NACA TN 3388) 

PRELIMINARY INVESTIGATION OF A SUBMERGED 
AIR SCOOP UTILIZING BOUNDARY-LAYER 
SUCTION TO OBTAIN INCREASED PRESSURE 
RECOVERY. Mark R. Nichols and P. Kenneth 
Pierpont. April 1955. 72p. diagrs., photos., 
2 tabs. (NACA TN 3437. Formerly RM L50A13) 



62 AERODYNAMICS 



Propellers 
(1.5) 



PROPELLER SECTION AERODYNAMIC CHARAC- 
TERISTICS AS DETERMINED BY MEASURING THE 
SECTION SURFACE PRESSURES ON AN NACA 
10-(3)(08)-03 PROPELLER UNDER OPERATING 
CONDITIONS. Albert J. Evans. November 8, 1950. 
162p. diagrs., 10 tabs. (NACA RM L50H03) 

ANALYTICAL STUDY OF STATIC AND LOW- 
SPEED PERFORMANCE OF THIN PROPELLERS 
USING TWO-SPEED GEAR RATIOS TO OBTAIN 
OPTIMUM ROTATIONAL SPEEDS. Jean Oilman, Jr. 
November 1952. 52p. diagrs., 4 tabs. (NACA 
RM L52I09) 

CALCULATION OF AERODYNAMIC FORCES ON AN 
INCLINED DUAL-ROTATING PROPELLER. John 
L. Crigler and Jean Gilman, Jr. June 1953. 24p. 
diagrs. (NACA RM L53D30) 

AERODYNAMIC INVESTIGATION OF A FOUR- 
BLADE PROPELLER OPERATING THROUGH AN 
ANGLE -OF-ATTACK RANGE FROM 0° TO 180°. 
H. Clyde McLemore and Michael D. Cannon. June 
1954. 62p. diagrs., photo. (NACA TN 3228) 



THEORY 
(1.5.1) 



APPLICATION OF THEODORSEN'S PROPELLER 
THEORY TO THE CALCULATION OF THE PER- 
FORMANCE OF DUAL-ROTATING PROPELLERS. 
Jean Gilman, Jr. March 15, 1951. 31p. diagrs. 
(NACA RM L51A17) 

PROPELLER LIFT AND THRUST DISTRIBUTION 
FROM WAKE SURVEYS OF STAGNATION CONDI- 
TIONS. Robert E. Davidson. January 1952. 19p. 
diagrs. (NACA RM L51K29) 

PROPELLER INDUCED ANGLES OF ATTACK AND 
SECTION ANGLES OF ATTACK FOR THE NACA 
10-(3)(066)-03, 10-(3)(049)-03, 10-(3)(090)-03, 
10-(5)(066)-03, AND 10-(0)(066)-03 PROPELLERS. 
William B. Igoe and Robert E. Davidson. May 1952. 
80p. diagrs., 10 tabs. (NACA RM L51L06) 

AERODYNAMIC INVESTIGATION OF A FOUR- 
BLADE PROPELLER OPERATING THROUGH 4N 
ANGLE-OF-ATTACK RANGE FROM 0° TO 180°. 
H. Clyde McLemore and Michael D. Cannon. June 
1954. 62p. diagrs., photo. (NACA TN 3228) 



OSCILLATING PRESSURES NEAR A STATIC 
PUSHER PROPELLER AT TIP MACH NUMBERS UP 
TO 1.20 WITH SPECIAL REFERENCE TO THE EF- 
FECTS OF THE PRESENCE OF THE WING. Harve;? 
H. Hubbard and Leslie W. Lassiter. July 1954. 
35p. diagrs., photos., tab. (NACA TN 3202) 

CIRCUMFERENTIAL DBTRIBUTION OF 
PROPELLER -SLIPSTREAM TOTAL -PRESSURE 
RISE AT ONE RADIAL STATION OF A TWIN- 
ENGINE TRANSPORT AIRPLANE. A. W. Vogeley 
and H. A. Hart. April 1955. 24p. diagrs., photos. 
(NACA TN 3432) 



DESIGN VARIABLES 
(1.5.2) 

INVESTIGATION OF THE NACA 4-(4)(06)-057-45A 
AND NACA 4-(4)(06)-057-45B TWO-BLADE SWEPT 
PROPELLERS AT FORWARD MACH NUMBERS TO 
0.925. James B. Delano and Daniel E. Harrison. 
February 6, 1950. 44p. diagrs., photos. (NACA 
RM L9L05) 

A DISCUSSION OF THE DESIGN OF HIGHLY SWEPT 
PROPELLER BLADES. Richard T. Whitcomb. 
May 4, 1950. 31p. diagrs., photos. (NACA 
RM L50A23) 

A WIND-TUNNEL INVESTIGATION OF THE AERO- 
DYNAMIC CHARACTERISTICS OF A FULL-SCALE 
SWEPTBACK PROPELLER AND JWO RELATED 
STRAIGHT PROPELLERS. Albert J. Evans and 
George Liner. January 4, 1951. 102p. diagrs., 
photos., tab. (NACA RM L50J05) 

THE TORSIONAL DEFLECTIONS OF SEVERAL 
PROPELLERS UNDER OPERATING CONDITIONS. 
W. H. Gray and A. E. AUis. June 1951. 56p. 
diagrs., photos., tab. (NACA RM L51A19) 

THE EFFECTS OF VARIOUS PARAMETERS, 
INCLUDING MACH NUMBER, ON PROPELLER- 
BLADE FLUTTER WITH EMPHASIS ON STALL 
FLUTTER. John E. Baker. January 1955. 40p. 
diagrs., 3 tabs. (NACA TN 3357. Formerly 
RM L50L12b) 



BLADE SECTIONS 
(1.5.2.1) 



INVESTIGATION OF THE NACA 4-(3)(08)-03 TWO- 
BLADE PROPELLER AT FORWARD MACH NUM- 
BERS TO 0.925. James B. Delano and Francis G. 
Morgan, Jr. November 2, 1949. 30p. diagrs. , 
photos. (NACA RM L9I06) 

PRESSURE DISTRIBUTIONS ON THE BLADE SEC- 
TIONS OF THE NACA 10-(3)(066)-033 PROPELLER 
UNDER OPERATING CONDITIONS. Julian D. 
Maynard and Maurice P. Murphy. January 24, 1950. 
166p. diagrs., photos., 12 tabs. (NACA RM L9L12) 

PRESSURE DISTRIBUTIONS ON THE BLADE SEC- 
TIONS OF THE NACA 10-(3)(049)-033 PROPELLER 
UNDER OPERATING CONDITIONS. W. H. Gray 
and Robert M. Hunt. February 14, 1950. 120p. 
diagrs., 11 tabs. (NACA RM L9L23) 

PRESSURE DISTRIBUTIONS ON THE BLADE SEC- 
TIONS OF THE NACA 10-(3)(090)-03 PROPELLER 
UNDER OPERATING CONDITIONS. Peter J. 
Johnson. March 22, 1950. 90p. diagrs., 10 tabs. 
(NACA RM L50A26) 

PRESSURE DISTRIBUTIONS ON THE BLADE 
SECTIONS OF THE NACA 10-(5)(066)-03 PROPEL- 
LER UNDER OPERATING CONDITIONS. Albert J. 
Evans and Wallace Luchuk. April 18, 1950. 99p. 
diagrs., 10 tabs. (NACA RM L50B2i) 



AERODYNAMICS 
PROPELLERS (1.5) 



63 



Blade Sections 
(Cont. ) ■ 



Design Variables 



PRESSURE DISTRIBUTIONS ON THE BLADE 
SECTIONS OF THE NACA 10-(0)(066)-03 PROPEL- 
LER UNDER OPERATING CONDITIONS. Seymour 
Steinberg and Robert W. Milling. May 18, 1950. 
89p. dlagrs., 11 tabs. (NACA RM L50C03) 

EFFECT OF COMPRESSIBILITY AND CAMBER AS 
DETERMINED FROM AN INVESTIGATION OF THE 
NACA 4-(3)(08)-03 AND 4-(5)(08)-03 TWO-BLADE 
PROPELLERS UP TO FORWARD MACH NUMBERS 
OF 0.925. MeMn M. Carmel, Francis G. Morgan, 
Jr. and Domenic A. Coppolino. June 29, 1950. 92p. 
diagrs., photo. (NACA RM L50D28) 

PROPELLER SECTION AERODYNAMIC CHARAC- 
TERISTICS AS DETERMINED BY MEASURING THE 
SECTION SURFACE PRESSURES ON AN NACA 
10-(3)(08)-03 PROPELLER UNDER OPERATING 
CONDITIONS. Albert J. Evans. November 8, 1950. 
162p. diagrs., 10 tabs. (NACA RM L50H03) 

PROPELLER INDUCED ANGLES OF ATTACK AND 
SECTION ANGLES OF ATTACK FOR THE NACA 
10-(3)(066)-03, 10-{3)(049)-03, 10-(3)(090)-03, 
10-(5)(066)-03, AND 10-(0)(066)-03 PROPELLERS. 
William B. Igoe and Robert E. Davidson. May 1952. 
80p. diagrs., 10 tabs. (NACA RM L51L06) 

AERODYNAMIC CHARACTERISTICS OF NACA 0012 
AIRFOIL SECTION AT ANGLES OF ATTACK FROM 
0° TO 180°. Chris C. Critzos, Harry H. Heyson 
and Robert W. Boswinkle, Jr. January 1955. 21p. 
diagrs. (NACA TN 3361) 



BLADE PLAN FORMS 
(1. 5.2,4) 



A DISCUSSION OF THE DESIGN OF HIGHLY SWEPT 
PROPELLER BLADES. Richard T. Whltcomb. 
May 4, 1950. 31p. diagrs., photos. (NACA 
RM L50A23) 

A WIND-TUNNEL INVESTIGATION OF THE AERO- 
DYNAMIC CHARACTERISTICS OF A FULL-SCALE 
SWEPTBACK PROPELLER AND TWO RELATED 
STRAIGHT PROPELLERS. Albert J. Evans and 
George Liner. January 4, 1951. 102p. diagrs., 
photos., tab. (NACA RM L50J05) 



MACH NUMBER EFFECTS 
(1.5.2.5) 



INVESTIGATION OF THE NACA 4-(5)(08)-03 TWO- 
BLADE PROPELLER AT FORWARD MACH NUM- 
BERS TO 0.925. James B. Delano and Melvin M. 
Carmel. September 15, 1949. 61p. diagrs., photo. 
(NACA RM L9G06a) 

INVESTIGATION OF THE NACA 4-(4)(06)-04 TWO- 
BLADE PROPELLER AT FORWARD MACH NUM- 
BERS TO 0.925. James B. Delano and Daniel E. 
Harrison. October 28, 1949. 39p. diagrs., photos. 
(NACA RM L9I07) 



INVESTIGATION OF THE NACA 4-(3)(08)-03 TWO- 
BLADE PROPELLER AT FORWARD MACH NUM- 
BERS TO 0.925. James B. Delano and Francis G. 
Morgan, Jr. November 2, 1949. 30p. diagrs. , 
photos. (NACA RM L9I06) 

PRESSURE DISTRIBUTIONS ON THE BLADE SEC- 
TIONS OF THE NACA 10-(3)(066)-033 PROPELLER 
UNDER OPERATING CONDITIONS. Julian D. 
Maynard and Maurice P. Murphy. January 24, 1950. 
166p. diagrs., photos., 12 tabs. (NACA RM L9L12) 

INVESTIGATION OF THE NACA 4-(4)(06)-057-45A 
AND NACA 4-(4)(06)-057-45B TWO-BLADE SWEPT 
PROPELLERS AT FORWARD MACH NUMBERS TO 
0.925. James B. Delano and Daniel E. Harrison. 
February 6, 1950. 44p. diagrs., photos. (NACA 
RM L9L05) 

PRESSURE DISTRIBUTIONS ON THE BLADE SEC- 
TIONS OF THE NACA 10-(3)(049)-033 PROPELLER 
UNDER OPERATING CONDITIONS. W. H. Gray 
and Robert M. Hunt. February 14, 1950. 120p. 
diagrs., 11 tabs. (NACA RM L9L23) 

PRESSURE DISTRIBUTIONS ON THE BLADE SEC- 
TIONS OF THE NACA 10-(3)(090)-03 PROPELLER 
UNDER OPERATING CONDITIONS. Peter J. 
Johnson. March 22, 1950. 90p. diagrs., 10 tabs. 
(NACA RM L50A26) 

PRESSURE DISTRIBUTIONS ON THE BLADE 
SECTIONS OF THE NACA 10-(5)(066)-03 PROPEL- 
LER UNDER OPERATING CONDITIONS. Albert J. 
Evans and Wallace Luchuk. April 18, 1950. 99p. 
diagrs., 10 tabs. (NACA RM L50B21) 

PRESSURE DISTRIBUTIONS ON THE BLADE 
SECTIONS OF THE NACA 10-(0)(066)-03 PROPEL- 
LER UNDER OPERATING CONDITIONS. Seymour 
Steinberg and Robert W. Milling. May 18, 1950. 
89p. diagrs., 11 tabs. (NACA RM L50CO3) 

INVESTIGATION OF THE NACA 3-(3)(05)-05 
EIGHT-BLADE DUAL-ROTATING PROPELLER AT 
FORWARD MACH NUMBERS TO 0.925. Robert J. 
Piatt, Jr. and Robert A. Shiunaker. June 19, 1950. 
42p. diagrs., photo. (NACA RM L50D21) 

EFFECT OF COMPRESSIBILITY AND CAMBER AS 
DETERMINED FROM AN INVESTIGATION OF THE 
NACA 4-(3)(08)-03 AND 4-(5)(08)-03 TWO-BLADE 
PROPELLERS UP TO FORWARD MACH NUMBERS 
OF 0.925. Melvin M. Carmel, Francis G. Morgan, 
Jr. and Domenic A. Coppolino. June 29, 1950. 92p. 
diagrs., photo. (NACA Rfci L50D28) 

PROPELLER SECTION AERODYNAMIC CHARAC- 
TERISTICS AS DETERMINED BY MEASURING THE 
SECTION SURFACE PRESSURES ON AN NACA 
10-(3)(08)-03 PROPELLER UNDER OPERATING 
CONDITIONS. Albert J. Evans. November 8, 1950. 
162p. diagrs., 10 tabs. (NACA RM L50H03) 

A WIND-TUNNEL INVESTIGATION OF THE AERO- 
DYNAMIC CHARACTERISTICS OF A FULL-SCALE 
SWEPTBACK PROPELLER AND TWO RELATED 
STRAIGHT PROPELLERS. Albert J. Evans and 
George Liner. January 4, 1951. 102p. diagrs. 
photos., tab. (NACA RM L50J05) 

APPLICATION OF THEODORSEN'S PROPELLER 
THEORY TO THE CALCULATION OF THE PER- 
FORMANCE OF DUAL-ROTATING PROPELLERS. 
Jean Oilman, Jr. March 15, 1951. 31p. diagrs. 
(NACA RM L51A17) 

THRUST LOADING OF THE NACA 3-(3)(05)-05 
EIGHT -BLADE DUAL-ROTATING PROPELLER AS 
DETERMINED FROM WAKE SURVEYS. Robert J. 
Piatt, Jr. October 1952. 44p. diagrs., photo. 
(NACA RM L52I03) 



AERODYNAMICS 
64 PROPELLERS (1.5) 



Mach Number Effects - Design 
Variables (Cont. ) 

ANALYTICAL STUDY OF STATIC AND LOW- 
SPEED PERFORMANCE OF THIN PROPELLERS 
USING TWO-SPEED GEAR RATIOS TO OBTAIN 
OPTIMUM ROTATIONAL SPEEDS. Jean Gilman, Jr. 
November 1952. 52p. diagrs., 4 tabs. (NACA 
RM L52I09) 

INVESTIGATION OF AN NACA 4-(5)(05)-041 FOUR- 
BLADE PROPELLER WITH SEVERAL SPINNERS AT 
MACH NUMBERS UP TO 0.90. Robert M. Reynolds, 
Donald A. Buell and John H. Walker. December 
1952. 86p. diagrs., photos., 6 tabs. (NACA 
RM A52I19a) 

AERODYNAMIC INVESTIGATION OF A FOUR- 
BLADE PROPELLER OPERATING THROUGH AN 
ANGLE-OF-ATTACK RANGE FROM QO TO 180°. 
H. Clyde McLemore and Michael D. Cannon. June 
1954. 62p. diagrs., photo. (NACA TN 3228) 

OSCILLATING PRESSURES NEAR A STATIC 
PUSHER PROPELLER AT TIP MACH NUMBERS UP 
TO 1.20 WITH SPECIAL REFERENCE TO THE EF- 
FECTS OF THE PRESENCE OF THE WING. Harvey 
H. Hubbard and Leslie W. Lasslter. July 1954. 
35p. diagrs., photos., tab. (NACA TN 3202) 

MEASUREMENTS OF FREE -SPACE OSCILLATING 
PRESSURES NEAR A PROPELLER AT FLIGHT 
MACH NUMBERS TO 0.72. Arthur W. Vogeley and 
Max C. Kurbjun. May 1955. 24p. diagrs., photos., 
tab. (NACA TN 3417) 



PUSHER 
(1.5.2.6) 



AN INVESTIGATION OF PROPELLER VIBRATIONS 
EXCITED BY WING WAKES. W. H. Gray and 
William Solomon. January 1952. 31p. diagrs., 
photo., tab. (NACA RM L51G13) 

OSCILLATING PRESSURES NEAR A STATIC 
PUSHER PROPELLER AT TIP MACH NUMBERS UP 
TO 1.20 WITH SPECIAL REFERENCE TO THE EF- 
FECTS OF THE PRESENCE OF THE WING. Harvey 
H. Hubbard and Leslie W. Lassiter. July 1954. 
35p. diagrs., photos., tab. (NACA TN 3202) 



DUAL ROTATION 
(1.5.2.7) 



THE EFFECT OF THE PROPELLER SLIPSTREAM 
ON THE CHARACTERISTICS OF SUBMERGED 
INLETS. Noel K. Delany. September 9, 1949. 
41p. diagrs., photos. (NACA RM A9G15) 

INVESTIGATION OF THE NACA 3-(3)(05)-05 
EIGHT-BLADE DUAL-ROTATING PROPELLER AT 
FORWARD MACH NUMBERS TO 0.925. Robert J. 
Piatt, Jr. and Robert A. Shumaker. J(une 19, 1950. 
42p. diagrs., photo. (NACA RM L50D2"l) 

APPLICATION OF THEODORSEN'S PROPELLER 
THEORY TO THE CALCULATION OF THE PER- 
FORMANCE OF DUAL-ROTATING PROPELLERS. 
Jean Gilman, Jr. March 15, 1951. 31p. diagrs. 
(NACA RM L51A17) 



EFFECTS OF PROPELLER-SHANK GEOMETRY 
AND PROPELLER-SPINNER-JUNCTURE CONFIG- 
URATION ON CHARACTERBTICS OF AN NACA 1- 
SERIES COWLING-SPINNER COMBINATION WITH 
AN EIGHT -BLADE DUAL-ROTATION PROPELLER. 
Arvid L. Keith, Jr., Gene J. Bingham and Arnold J. 
Rubin. September 1951. 73p. diagrs., photos., 5 
tabs. (NACARM L51F26) 

THRUST LOADING OF THE NACA 3-(3)(05)-05 
EIGHT -BLADE DUAL-ROTATING PROPELLER AS 
DETERMINED FROM WAKE SURVEYS. Robert J. 
Piatt, Jr. October 1952. 44p. diagrs., photo. 
(NACA RM L52I03) 

CALCULATION OF AERODYNAMIC FORCES ON AN 
INCLINED DUAL-ROTATING PROPELLER. John 
L. Crigler and Jean Gilman, Jr. June 1953. 24p. 
diagrs. (NACA RM L53D30) 

EFFECTS OF COMPRESSIBILITY AT MACH NUM- 
BERS UP TO 0.8 ON INTERNAL-FLOW CHARAC- 
TERISTICS OF A COWLING-SPINNER COMBINA- 
TION EQUIPPED WITH AN EIGHT-BLADE DUAL- 
ROTATION PROPELLER. Gene J. Bingham and 
Arvid L. Keith, Jr. June 1953. 39p. diagrs., 
photos. (NACA RM L53E12) 



INTERFERENCE OF BODIES 
(1.5.2.8) 



AN INVESTIGATION OF PROPELLER VIBRATIONS 
EXCITED BY WING WAKES. W. H. Gray and 
William Solomon. January 1952. 3 Ip. diagrs., 
photo., tab. (NACA RM L51G13) 

INVESTIGATION OF AN NACA 4-(5)(05)-041 FOUR- 
BLADE~PROPELLER WITH SEVERAL SPINNERS AT 
MACH NUMBERS UP TO 0.90. Robert M. Reynolds, 
Donald A. Buell and John H. Walker. December 
1952. 86p. diagrs., photos., 6 tabs. (NACA 
RM A52I19a) 

OSCILLATING PRESSURES NEAR A STATIC 
PUSHER PROPELLER AT TIP MACH NUMBERS UP 
TO 1.20 WITH SPECIAL REFERENCE TO THE EF- 
FECTS OF THE PRESENCE OF THE WING. Harvey 
H. Hubbard and Leslie W. Lasslter. July 1954. 
35p. diagrs., photos., tab. (NACA TN 3202) 

CIRCUMFERENTIAL DISTRIBUTION OF 
PROPELLER-SLIPSTREAM TOTAL -PRESSURE 
RISE AT ONE RADIAL STATION OF A TWIN- 
ENGINE TRANSPORT AIRPLANE. A. W. Vogeley 
and H. A. Hart. April 1955. 24p. diagrs., photos. 
(NACA TN 3432) 

ON THE CALCULATION OF THE 1- P OSCILLATING 
AERODYNAMIC LOADS ON SINGLE -ROTATION 
PROPELLERS IN PITCH ON TRACTOR AIRPLANES. 
Vernon L. Rogallo and Paul F. Yaggy. May 1955. 
28p. diagrs., photo. (NACA TN 3395) 



PITCH AND YAW 
(1.5.2.9) 



CALCULATION OF AERODYNAMIC FORCES ON AN 
INCLINED DUAL-ROTATING PROPELLER. John 
L. Crigler and Jean .'(jtlman, Jr. June 1953. 24p. 
diagrs. (NACA RM L53D30) 



AERODYNAMICS 
PROPELLERS (1.5) 



65 



Pitch and Yaw 
(Cont. ) 



Design Variables 



AERODYNAMIC INVESTIGATION OF A FOUR- 
BLADE PROPELLER OPERATING THROUGH AN 
ANGLE-OF-ATTACK RANGE FROM 0° TO 180°. 
H. Clyde McLemore and Michael D. Cannon. June 
1954. 62p. diagrs., photo. (NACA TN 3228) 

INVESTIGATION OF THE AERODYNAMIC CHARAC- 
TERISTICS OF A MODEL WING-PROPELLER COM- 
BINATION AND OF THE WING AND PROPELLER 
SEPARATELY AT ANGLES OF ATTACK UP TO 90°. 
JohnW. Draper and Richard E. Kuhn. November 
1954. 72p. diagrs., photos., tab. (NACA TN 3304) 



DESIGNATED TYPES 
(1.5.3) 



INVESTIGATION OF THE NACA 4-(5)(08)-03 TWO- 
BLADE PROPELLER AT FORWARD MACH NUM- 
BERS TO 0.925. James B. Delano and Melvin M. 
Carmel. September 15, 1949. 61p. diagrs., photo. 
(NACA RM L9G06a) 

INVESTIGATION OF THE NACA 4-(4)(06;-04 TWO- 
BLADE PROPELLER AT FORWARD MACH NUM- 
BERS TO 0.925. James B. Delano and Daniel E. 
Harrison. October 28, 1949. 39p. diagrs., photos. 
(NACA RM L9I07) 

INVESTIGATION OF THE NACA 4-(3)(08)-03 TWO- 
BLADE PROPELLER AT FORWARD MACH NUM- 
BERS TO 0.925. James B. Delano and Francis G. 
Morgan, Jr. November 2, 1949. 30p. diagrs. , 
photos. (NACA RM L9I06) 

INVESTIGATION OF THE NACA 4-(4)(06)-057-45A 
AND NACA 4-(4)(06)-057-45B TWO-BLADE SWEPT 
PROPELLERS AT FORWARD MACH NUMBERS TO 
0.925. James B. Delano and Daniel E. Harrison. 
February 8, 1950. 44p. diagrs., photos. (NACA 
RM L9L05) 

EFFECT OF COMPRESSIBILITY AND CAMBER AS 
DETERMINED FROM AN INVESTIGATION OF THE 
NACA 4-(3)(08)-03 AND 4-(5)(08)-03 TWO-BLADE 
PROPELLERS UP TO FORWARD MACH NUMBERS 
OF 0.925. Melvin M. Carmel, Francis G. Morgan, 
Jr. and Domenic A. Coppolino. June 29, 1950. 92p. 
diagrs., photo. (NACA BM L50D28) 

A WIND-TUNNEL INVESTIGATION OF THE AERO- 
DYNAMIC CHARACTERISTICS OF A FULL-SCALE 
SWEPTBACK PROPELLER AND TWO RELATED 
STRAIGHT PROPELLERS. Albert J. Evans and 
George Liner. January 4, 1951. 102p. diagrs., 
photos., tab. (NACA RM L50J05) 

THRUST LOADING OF THE NACA 3-(3)(Q5)-05 
EIGHT -BLADE DUAL-ROTATING PROPELLER AS 
DETERMINED FROM WAKE SURVEYS. Robert J. 
Piatt, Jr. October 1952. 44p. diagrs., photo. 
(NACA RM L52I03) 

INVESTIGATION OF AN NACA 4-(5)(05)-041 FOUR- 
BLADE PROPELLER WITH SEVERAL SPINNERS AT 
MACH NUMBERS UP TO 0.90. Robert M. Reynolds, 
Donald A. Buell and John H. Walker. December 
1952. 86p. diagrs., photos., 6 tabs. (NACA 
RM A52I19a) 



CALCULATION OF AERODYNAMIC FORCES ON AN 
INCLINED DUAL-ROTATING PROPELLER. John 
L. Crigler and Jean Oilman, Jr. June 1953. 24p. 
diagrs. (NACA RM L53D30) 



SLIPSTREAM 
(1.5.4) 



INVESTIGATION OF THE NACA 4-(5)(08)-03 TWO- 
BLADE PROPELLER AT FORWARD MACH NUM- 
BERS TO 0.925. James B. Delano and Melvin M. 
Carmel. September 15, 1949. 61p. diagrs., photo. 
(NACA RM L9G06a) 

EFFECT OF COMPRESSIBILITY AND CAMBER AS 
DETERMINED FROM AN INVESTIGATION OF THE 
NACA 4-(3)(08)-03 AND 4-(5)(08)-03 TWO-BLADE 
PROPELLERS UP TO FORWARD MACH NUMBERS 
OF 0.925. Melvin M. Carmel, Francis G. Morgan, 
Jr. and Domenic A. Coppolino. June 29, 1950. 92p. 
diagrs., photo. (NACA IM L50D28) 

PROPELLER LIFT AND THRUST DISTRIBUTION 
FROM WAKE SURVEYS OF STAGNATION CONDI- 
TIONS. Robert E. Davidson. January 1952. 19p. 
diagrs. (NACA RM L51K29) 

THRUST LOADING OF THE NACA 3-(3)(05)-05 
EIGHT -BLADE DUAL-ROTATING PROPELLER AS 
DETERMINED FROM WAKE SURVEYS. Robert J. 
Piatt, Jr. October 1952. 44p. diagrs., photo. 
(NACA RM L52I03) 

PRELIMINARY RESULTS FROM FLOW-FIELD 
MEASUREMENTS AROUND SINGLE AND TANDEM 
ROTORS IN THE LANGLEY FULL-SCALE TUNNEL. 
Harry H. Heyson. November 1954. 19p. diagrs., 
photos. (NACA TN 3242) 

INVESTIGATION OF THE AERODYNAMIC CHARAC- 
TERISTICS OF A MODEL WING-PROPELLER COM- 
BINATION AND OF THE WING AND PROPELLER 
SEPARATELY AT ANGLES OF ATTACK UP TO 90°. 
JohnW. Draper and Richard E. Kuhn. November 
1954. 72p. diagrs., photos., Ub. (NACA TN 3304) 

AN INVESTIGATION OF A WING-PROPELLER CON- 
FIGURATION EMPLOYING LARGE-CHORD PLAIN 
FLAPS AND LARGE -DIAMETER PROPELLERS FOR 
LOW -SPEED FLIGHT AND VERTICAL TAKE-OFF. 
Richard E. Kuhn and John W. Draper. December 

1954. 94p. diagrs., photos. (NACA TN 3307) 

SOME EFFECTS OF PROPELLER OPERATION AND 
LOCATION ON ABILITY OF A WING WITH PLAIN 
FLAPS TO DEFLECT PROPELLER SLIPSTREAMS 
DOWNWARD FOR VERTICAL TAKE-OFF. John W. 
Draper and Richard E. Kuhn. January 1955. 28p. 
diagrs., photo. (NACA TN 3360) 

INVESTIGATION OF EFFECTIVENESS OF LARGE - 
CHORD SLOTTED FLAPS IN DEFLECTING 
PROPELLER SLIPSTREAMS DOWNWARD FOR 
VERTICAL TAKE-OFF AND LOW -SPEED FLIGHT. 
Richard E. Kuhn and John W. Draper. January 

1955. 42p. diagrs., photo., tab. (NACA TN 3364) 

CIRCUMFERENTIAL DISTRIBUTION OF 
PROPELLER-SLIPSTREAM TOTAL-PRESSURE 
RISE AT ONE RADIAL STATION OF A TWIN- 
ENGINE TRANSPORT AIRPLANE. A. W. Vogeley 
and H. A. Hart. April 1955. 24p. diagrs., photos. 
(NACA TN 3432) 



AERODYNAMICS 
66 PROPELLERS (1. 5) 



OPERATING CONDITIONS 
(1.5.6) 

THE EFFECT OF BLADE-SECTION CAMBER ON 
THE STATIC CHARACTERISTICS OF THREE NACA 
PROPELLERS. John H. Wood and John M. Swihart. 
April 1952. 40p. diagrs., photos. (NACA RM 
L51L28) 

ANALYTICAL STUDY OF STATIC AND LOW- 
SPEED PERFORMANCE OF THIN PROPELLERS 
USING TWO-SPEED GEAR RATIOS TO OBTAIN 
OPTIMUM ROTATIONAL SPEEDS. Jean Oilman, Jr. 
November 1952. 52p. diagrs., 4 tabs. (NACA 
RM L52I09) 

AERODYNAMIC INVESTIGATION OF A FOUR- 
BLADE PROPELLER OPERATING THROUGH AN 
ANGLE-OF-ATTACK RANGE FROM 0° TO 180°. 
H. Clyde McLemore and Michael D. Cannon. June 
1954. 62p. diagrs., photo. (NACA TN 3228) 

THE EFFECTS OF VARIOUS PARAMETERS, 
INCLUDING MACH NUMBER, ON PROPELLER- 
BLADE FLUTTER WITH EMPHASIS ON STALL 
FLUTTER. John E. Baker. January 1955. 40p. 
diagrs., 3 tabs. (NACA TN 3357. Formerly 
RM L50L12b) 

CIRCUMFERENTIAL DISTRIBUTION OF 
PROPELLER-SLIPSTREAM TOTAL -PRESSURE 
RISE AT ONE RADUL STATION OF A TWIN- 
ENGINE TRANSPORT AIRPLANE. A. W. Vogeley 
and H. A. Hart. April 1955. 24p. diagrs., photos. 
(NACA TN 3432) 

ON THE CALCULATION OF THE 1- P OSCILLATING 
AERODYNAMIC LOADS ON SINGLE -ROTATION 
PROPELLERS IN PITCH ON TRACTOR AIRPLANES. 
Vernon L. Rogallo and Paul F. Yaggy. May 1955. 
28p. diagrs., photo. (NACA TN 3395) 



PROPELLER-SPINNER-COWL 

COMBINATIONS 

(1.5.7) 



EFFECTS OF PROPELLER-SHANK GEOMETRY 
AND PROPELLER-SPINNER-JUNCTURE CONFIG- 
URATION ON CHARACTERISTICS OF AN NACA 1- 
SERIES COWLING-SPINNER COMBINATION WITH 
AN EIGHT -BLADE DUAL-ROTATION PROPELLER. 
Arvid L. Keith, Jr., Gene J. Bingham and Arnold J. 
Rubin. September 1951. 73p. diagrs., photos., 5 
tabs. (NACA RM L51F26) 



EFFECTS OF PROPELLER-SPINNER JUNCTURE 
ON THE PRESSURE -RECOVERY CHARACTERIS- 
TICS OF AN NACA 1 -SERIES D-TYPE COWL IN 
COMBINATION WITH A FOUR-BLADE SINGLE- 
ROTATION PROPELLER AT MACH NUMBERS UP 
TO 0.83 AND AT AN ANGLE OF ATTACK OF 0°. 
Robert I. Sammonds and Ashley J. Molk. June 1952. 
45p. diagrs., photos., tab. (NACA RM A52D01a) 



INVESTIGATION OF AN NACA 4-(5)(05)-041 FOUR- 
BLADE PROPELLER WITH SEVERAL SPINNERS AT 
MACH NUMBERS UP TO 0.90. Robert M. Reynolds, 
Donald A. Buell and John H. Walker. December 
1952. 86p. diagrs., photos., 6 tabs. (NACA 
RM A52I19a) 



EFFECTS OF COMPRESSIBILITy AT MACH NUM- 
BERS UP TO 0.8 ON INTERNAL-FLOW CHARAC- 
TERISTICS OF A COWLING-SPINNER COMBINA- 
TION EQUIPPED WITH AN EIGHT -BLADE DUAL- 
ROTATION PROPELLER. Gene J. Bingham and 
Arvid L. Keith, Jif. June 1953. 39p. diagrs., 
photos. (NACA RM L53E12) 



AERODYNAMICS 67 



Rotating Wings 
(1.6) 



AERODYNAMIC CHARACTERISTICS OF NACA0012 
AIRFOIL SECTION AT ANGLES OF ATTACK FROM 
QO TO 180°. Chris C. Critzos, Harry H. Heyson 
and Robert W. Boswinkle, Jr. January 1955. 21p. 
diagrs. (NACA TN 3361) 

THEORY 
(l.6.l) 

REVIEW OF INFORMATION ON INDUCED FLOW OF 
A LIFTING ROTOR. Alfred Gessow. August 1954. 
16p. diagrs., photo., tab. <NACA TN 3238) 



PRELIMINARY RESULTS FROM FLOW-FIELD 
MEASimEMENTS AROUND SINGLE AND TANDEM 
ROTORS IN THE LANGLEY FULL-SCALE TUNNEL. 
Harry H. Heyson. November 1954. 19p. diagrs., 
photos. (NACA TN 3242) 

CHARTS FOR ESTIMATING PERFORMANCE OF 
HIGH-PERFORMANCE HEUCOPTERS. Alfred 
Gessow and Robert J. Tapscott. January 1955. 
36p. diagrs. (NACA TN 3323) 

A METHOD FOR STUDYING THE TRANSIENT 
BLADE -f LAPPING BEHAVIOR OF LIFTING ROTORS 
AT EXTREME OPERATING CONDITIONS. Alfred 
Gessow and Aimer D. Crim. January 1955. 27p. 
diagrs. (NACA TN 3366) 



EXPERIMENTAL STUDIES 



(1.6.2) 



DESCRIPTION AND INVESTIGATION OF A 
DYNAMIC MODEL OF THE XH-17 TWO-BLADE 
JET-DRIVEN HELICOPTER. George W. Brooks and 
Maurice A. Sylvester. March 14, 1951. 49p. 
diagrs., photos., 6 tabs. (NACA RM L50I21) 

WIND-TUNNEL STUDIES OF THE PERFORMANCE 
OF MULTIROTOR CONFIGURATIONS. Richard C. 
Dingeldeln. August 1954. lOp. diagrs., photo. 
(NACA TN 3236), 



REVIEW OF INFORMATION ON INDUCED FLOW OF 
A LIFTING ROTOR. Alfred Gessow. August 1954. 
16p. diagrs., photo., tab. (NACA TN 3238) 

THE EFFECT OF CONTROL STIFFNESS AND FOR- 
WARD SPEED ON THE FLUTTER OF A 1/10-SCALE 
DYNAMIC MODEL OF A TWO-BLADE JET -DRIVEN 
HELICOPTER ROTOR. George W. Brooks and 
Maurice A. Sylvester. April 1955. 38p. diagrs., 
photo., 3 tabs. (NACA TN 3376) 

A STUDY OF NORMAL ACCELERATIONS AND 
OPERATING CONDITIONS EXPERIENCED BY 
HELICOPTERS IN COMMERCIAL AND MILITARY 
OPERATIONS. Marlin E. Hazen. April 1955. 34p. 
diagrs., photos., 5 tabs. (NACA TN 3434) 

A DYNAMIC-MODEL STUDY OF THE EFFECT OF 
ADDED WEIGHTS AND OTHER STRUCTURAL VAR- 
IATIONS ON THE BLADE BENDING STRAINS OF AN 
EXPERIMENTAL TWO-BLADE JET-DRIVEN HELI- 
COPTER IN HOVERING AND FORWARD FLIGHT. 
John Locke McCarty and George W. Brooks. May 
1955. 1, 47p. diagrs., photo., 6 tabs. (NACA 
TN 3367) 



POWER DRIVEN 
(1.6.2.1) 

REDUCTION OF HELICOPTER PARASITE DRAG. 
Robert D. Harrington. August 1954. 8p. diagrs. 
(NACA TN 3234) 

WIND-TUNNEL STUDIES OF THE PERFORMANCE 
OF MULTIROTOR CONFIGURATIONS. Richard C. 
Dingeldeln. August 1954. 'lOp. diagrs., photo. 
(NACA TN 3236) 

HOVERING PERFORMANCE OF A HELICOPTER 
ROTOR USING NACA 8-H-12 AIRFOIL SECTIONS. 
Robert D. Powell, Jr. August 1954. 14p. diagrs., 
photos. (NACA TN 3237) 

PRELIMINARY RESULTS FROM FLOW-FIELD 
MEASUREMENTS AROUND SINGLE AND TANDEM 
ROTORS IN THE LANGLEY FULL-SCALE TUNNEL. 
Harry H. Heyson. November 1954. 19p. diagrs., 
photos. (NACA TN 3242) 



68 AERODYNAMICS 



Aircraft 
(1.7) 



AIRPLANES 
(1.7.0 



EFFECT OF CURRENT DESIGN TRENDS ON AIR- 
PLANE SPINS AND RECOVERIES. Anshal I. 
Neihouse. January 1952. 6p. diagrs. (NACA RM 
L52A09) 



COMPONENTS IN COMBINATION 
(1.7. I.l) 



FORCE AND LONGITUDINAL CONTROL CHARAC- 
TERISTICS OF A 1/16 - SCALE MODEL OF THE 
BELL XS-1 TRANSONIC RESEARCH AIRPLANE AT 
HIGH MACH NUMBERS. Axel T. Mattson. May 21, 
1947. 32p. diagrs., photo., tab. (NACA RM L7A03) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE - DYNAMIC PRESSURE AND COMPARISON 
OF POINT AND EFFECTIVE DOWNWASH AT THE 
TAIL OF THE D-558-1. Harold L. Robinson. 
November 4, 1948. 27p. diagrs. (NACA RM L8H05) 

AN ANALYSIS OF AVAILABLE DATA ON EFFECTS 
OF WING-FUSELAGE-TAIL AND WING-NACELLE 
INTERFERENCE ON THE DISTRIBUTION OF THE 
AIR LOAD AMONG COMPONENTS OF AIRPLANES. 
Bertram C. WoUner. April 11, 1949. 33p. diagrs., 
tab. (NACA RM L9B10) 

WIND-TUNNEL INVESTIGATION AT LOW SPEED 
TO DETERMINE AERODYNAMIC PROPERTIES OF 
A JETTISONABLE NOSE SECTION WITH CIRCULAR 
CROSS SECTION. Roscoe H. Goodwin. May 19, 
1950. 38p. diagrs., photos. (NACA RM L9J13) 

THE CALCULATION OF THE PATH OF A JETTI- 
SONABLE NOSE SECTION, Roscoe H. Goodwin. 
September 7, 1950. 35p. diagrs. (NACA RM L50G18) 

LOW -SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AIRPLANE - LONGITUDINAL 
CHARACTERISTICS. Noel K. Delany and Nora-Lpe 
F. Hayter. September 8, 1950. 80p. diagrs., 
photos., 2 tabs. (NACA RM A50G06) 

A STUDY OF THE FLOW FIELD BEHIND THE TRI- 
ANGULAR HORIZONTAL TAIL OF A CANARD AIR- 
PLANE AT APPROXIMATELY THE VERTICAL- 
TAIL LOCATION BY MEANS OF A TUFT GRID. 
Joseph L. Johnson, Jr. October 1952. 18p. diagrs., 
tab. (NACA RM L52H11) 

WING AND FUSELAGE LOADS MEASURED IN 
FLIGHT ON THE NORTH AMERICAN B-45 AND 
F-82 AIRPLANES. Paul W. Harper. February 
1953. 35p. diagrs., 4 tabs. (NACA RM L52L09) 

EFFECT OF HORIZONTAL-TAIL SPAN AND 
VERTICAL LOCATION ON THE AERODYNAMIC 
CHARACTERISTICS OF AN UNSWEPT TAIL 
ASSEMBLY IN SIDESLIP. Donald R. Riley. 1954. 
ii, 20p. diagrs., photos., tab. (NACA Rept. 1171. 
Formerly TN 2907) 



REDUCTION OF HELICOPTER PARASITE DRAG. 
Robert D. Harrington. August 1954. 8p. diagrs. 
(NACA TN 3234) 

CALCULATED SUBSONIC SPAN LOADS AND 
RESULTING STABILITY DERIVATIVES OF UN- 
SWEPT AND 45° SWEPTBACK TAIL SURFACES IN 
SIDESLIP AND IN STEADY ROLL. M. J. Queijo 
and Donald R. Riley. October 1954. llOp. 
diagrs., 2 tabs. (NACA TN 3245) 

ARRANGEMENT OF FUSIFORM BODIES TO RE- 
DUCE THE WAVE DRAG AT SUPERSONIC SPEEDS. 
Morris D. Friedman and Doris Cohen. November 
1954 23p. diagrs. (NACA TN 3345. Formerly 
RM A51I20) 

THEORETICAL CALCULATIONS OF THE LATERAL 
STABILITY DERIVATIVES FOR TRIANGULAR VER- 
TICAL TAILS WITH SUBSONIC LEADING EDGES 
TRAVELING AT SUPERSONIC SPEEDS. Percy J. 
Bobbitt. December 1954. 68p. diagrs., photos., 
5 tabs. (NACA TN 3240) 

A THEORETICAL INVESTIGATION OF THE 
SHORT -PERIOD DYNAMIC LONGITUDINAL 
STABILITY OF AIRPLANE CONFIGURATIONS 
HAVING ELASTIC WINGS OF 0° TO 60° SWEEP- 
BACK. Milton D. McLaughlin. December 1954. 
39p. diagrs., 2 tabs. (NACA TN 3251) 

THEORETICAL CALCULATIONS OF THE PRES- 
SURES, FORCES, AND MOMENTS DUE TO 
VARIOUS LATERAL MOTIONS ACTING ON THIN 
ISOLATED VERTICAL TAILS WITH SUPERSONIC 
LEADING AND TRAILING EDGES. Kenneth 
Margolis. March 1955. 43p. diagrs., 10 tabs. 
(NACA TN 3373) 



Wing-Fuselage 
(1.7.1.1.1) 



WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 1.53 OF AN AIRPLANE WITH A TRIANGU- 
LAR WING. Richard Scherrer and William R. 
Wlmbrow. January 23, 1948. 74p. diagrs., 
photos., 2 tabs. (NACA RM A7J05) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE. BASIC LONGITUDINAL STABILITY OF 
THE D-558-1. John B. Wright. May 12, 1948. 19p. 
diagrs.. t.b. (NACA RM L7K24) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE. LONGITUDINAL STABILITY AND CON- 
TROL OF THE D-558-1. John B. Wright. July 8, 
1948. 47p. diagrs., tab. (NACA RM LaC23) 

EFFECT OF WING SWEEP, TAPER, AND THICK- 
NESS RATIO ON THE TRANSONIC DRAG CHARAC- 
TERISTICS OF WING-BODY COMBINATIONS. Jim 
Rogers Thompson and Charles W. Mathews. 
December 31, 1948. 29p. diagrs,, photos., 2 tabs. 
(NACA RM L8K01) 



AERODYNAMICS 
AIRCRAFT (1.7) 69 



Wing-Fuselage - Airplanes (Cont. ) 



AN ANALYSIS OF AVAILABLE DATA ON EFFECTS 
OF WING-FUSEIAGE-TAIL AND WING-NACELLE 
INTERFERENCE ON THE DISTRIBUITON OF THE 
AIR LOAD AMONG COMPONENTS OF AIRPLANES. 
Bertram C. Wollner. April 11, 1949. 33p. diagrs., 
tab. (NACA RM L9B10) 

EFFECT OF SWEEPBACK ON THE LOW-SPEED 
STATIC AND ROLUNG STABILITY DERIVATIVES 
OF THIN TAPERED WINGS OF ASPECT RATIO 4. 
WiUlam Letko and Walter D. Wolhart. August 9, 
1949. 36p. diagrs., photo. (NACA RM L9F14) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER - 
CHORD LINE SWEPT BACK 45°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. Raymond 
D. Vogler. August 15, 1949. 22p. diagrs. (NACA 
RM L9F29a) 

PRELIMINARY WIND-TUNNEL INVESTIGATION AT 
HIGH -SUBSONIC SPEEDS OF PLANING-TAIL, 
BLENDED, AND AIRFOIL -FOREBODY SWEPT 
HULLS. John M. Riebe and Richard G. MacLeod. 
September 12, 1949. 33p. diagrs., photos., 3 tabs. 
(NACA RM L9D01) 

LOW-SPEED STATIC LATERAL STABILITY CHAR- 
ACTERISTICS OF A CANARD MODEL HAVING A 
60° TRIANGULAR WING AND HORIZONTAL TAIL. 
William R. Bates. November 23, 1949. 29p. 
diagrs., tab. (NACA RM L9J12) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER- 
CHORD LINE SWEPT BACK 35°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC-BUMP METHOD. Robert F. 
Thompson. January 25, 1950. 22p. diagrs., tab. 
(NACA RM L9L12a) 

AERODYNAMIC CHARACTERISTICS WITH FIXED 
AND FREE TRANSITION OF A MODIFIED DELTA 
WING IN COMBINATION WITH A FUSELAGE AT 
HIGH SUBSONIC SPEEDS. Edward C. Polhamus and 
Thomas J. King, Jr. May 2, 1950. 19p. diagrs., 
photos. (NACARML50C21) 

AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBSR OF 1.25 OF A 6-PERCENT-THICK TRIAN- 
GULAR WING AND 6- AND 9-PERCENT-THICK TRI- 
ANGULAR WINGS IN COMBINATION WriH A FUSE- 
LAGE. WING ASPECT RATIO 2.31, BICONVEX AIR- 
FOIL SECTIONS. Albert W. Hall and Garland J. 
Morris. May 5, 1950. 22p. diagrs., photo., 2 tabs. 
(NACA RM L50D05) 

INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
METHODS OF ALLEVIATING THE ADVERSE 
INTERFERENCE AT THE ROOT OF A SWEPT- 
BACKWDJG. LeeE. Boddy. August 10, 1950. 31p. 
diagrs., photos. (NACA RM A50E26) 

RESULTS OF FUGHT TESTS TO DETERMINE THE 
ZERO-LIFT DRAG CHARACTERISTICS OF A 60° 
DELTA WING WITH NACA 65-006 AIRFOIL SEC- 
TION AND VARIOUS DOUBLE -WEDGE SECTIONS 
AT MACH NUMBERS FROM 0.7 TO 1.6. Clement J. 
Welsh. August 11, 1950. 15p. diagrs., photo. 
(NACA RM L50F01) 

INVESTIGATION AT TRANSONIC SPEEDS OF A 
35-PERCENT -CHORD AILERON ON A TAPERED 
WEDGE-TYPE WING OF ASPECT RATIO 2.5 WITH 
AND WITHOUT A FUSELAGE. Thomas R. Turner 
and Joseph E. Fikes. September 8, 1950. 25p. 
diagrs. (NACA RM L50G13a) 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AT HIGH-SUBSONIC SPEEDS OF TWO 
MODELS OF A TRANSONIC RESEARCH AIRPLANE 
WITH WINGS AND HORIZONTAL TAILS OF ASPECT 
RATIOS 4.2 AND 2. Arvo A. Luoma and John B. 
Wright. September 29, 1950. 134p. diagrs., photos., 
3 tabs. (NACA RM L50H07) 

AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBER OF 1.38 OF FOUR WiNGS OF ASPECT 
RATIO 4 HAVING QUARTER-CHORD SWEEP 
ANGLES OF 0°, 35°, 45°, AND 60°. WUllam B. 
Kemp, Jr., Kenneth W. Goodson and Robert A. Booth. 
October 10, 1950. 41p. diagrs., photos., tab. 
(NACA RM L50G14) 

LOW-SPEED INVESTIGATION OF THE EFFECT OF 
SEVERAL FLAP AND SPOILER AILERONS ON THE 
LATERAL CHARACTERISTICS OF A 47.5° 
SWEPTBACK-WING - FUSELAGE COMBINATION 
AT A REYNOLDS NUMBER OF 4.4 x 10^. Jerome 
Pasamanick and Thomas B. Sellers. December 8, 
1950. 57p. diaws., photo. (NACA RM L50J20) 

LONGITUDINAL-CONTROL EFFECTIVENESS AND 
DOWNWASH CHARACTERISTICS AT A MACH NUM- 
BER OF 1.24 OF A 1/30-SCALE SEMISPAN MODEL 
OF THE BELL X-5 AIRPLANE AS DETERMINED BY 
THE NACA WING-FLOW METHOD: Richard H. 
Sawyer, Robert M. Kennedy and Garland J. Morris. 
January 8, 1951. 37p. diagrs., photos., tab. 
(NACA RM L50K15) 

NOTE ON FLUTTER OF A 60° DELTA WING 
ENCOUNTERED AT LOW-SUPERSONIC SPEEDS 
DURING THE FLIGHT OF A ROCKET-PROPELLED 
MODEL. William T. Lauten, Jr. and Grady L. 
Mitcham. May 14, 1951. 21p. diagrs., photos., 
5 tabs. (NACA RM L51B28) 

AN EXPERIMENTAL STUDY AT MODERATE AND 
HIGH SUBSONIC SPEEDS OF THE FLOW OVER 
WINGS WITH 30° AND 45° OF SWEEPBACK IN 
CONJUNCTION WITH A FUSELAGE. Richard T. 
Whitcomb. June 15, 1951. 56p. diagrs., photos. 
(NACA RM L50K27) 

AN EXPERIMENTAL STUDY OF MODERATE AND 
HIGH SUBSONIC SPEEDS OF THE FLOW OVER 
WINGS WITH 30° AND 45° OF SWEEPFORWARD 
IN CONJUNCTION WITH A FUSELAGE. Richard T. 
Whitcomb. June 15, 1951. 47p. diagrs., photo. 
(NACA RM L50K28) 

AN EXPERIMENTAL STUDY OF MODERATE AND 
HIGH SUBSONIC SPEEDS OF THE FLOW OVER AN 
UNSWEPT WING IN CONJUNCTION WITH A FUSE- 
LAGE. Richard T. Whitcomb. June 18, 1951. 35p. 
diagrs., photos. (NACA RM L50L07) 

CONTRIBUTIONS OF WING, TAIL, AND FUSELAGE 
TO THE AERODYNAMIC CHARACTERISTICS OF A 
SEMISPAN MODEL OF A SUPERSONIC AIRPLANE 
CONFIGURATION AT TRANSONIC SPEEDS FROM 
TESTS BY THE NACA WING-FLOW METHOD. 
Norman S. Sllsby and James M. McKay. July 1951. 
34p. diagrs., photos., tab. (NACA RM L51E01) 

COMPARISON OF AIRFOIL SECTIONS ON TWO 
TRIANGULAR-WING-FUSELAGE CONFIGURATIONS 
AT TRANSONIC SPEEDS FROM TESTS BY THE 
NACA WING-FLOW METHOD. Albert W. Hall and 
James M. McKay. August 1951. 23p. diagrs., 
photo., tab. (NACARM L51F01) 

THE EFFECTS ON THE AERODYNAMIC CHARAC- 
TERISTICS OF REVERSING THE WING OF A TRI- 
ANGULAR WING-BODY COMBINATION AT TRAN- 
SONIC SPEEDS AS DETERMINED BY THE NACA 
WING-FLOW METHOD. James M. McKay and 
Albert W. Hall. October 1951. 22p. diagrs., photo., 
2 tabs. (NACA RM L51H23) 



AERODYNAMICS 
70 AIRCRAFT (1. 7) 



Wing-Fuselage - Airplanes (Cont. ) 

LOAD DISTRIBUTION OVER A FUSELAGE IN COM- 
BINATION WITH A SWEPT WING AT SMALL 
ANGLES OF ATTACK AND TRANSONIC SPEEDS. 
Maurice D. White and Bonne C. Look. November 

1951. 26p. diagrs., photo., tab. (NACA RM 
A51H15) 

SUMMARY OF RESULTS OBTAINED BY 
TRANSONIC -BUMP METHOD ON EFFECTS OF 
PLAN FORM AND THICKNESS OF LIFT AND DRAG 
CHARACTERISTICS OF WINGS AT TRANSONIC 
SPEEDS. Edward C. Polhamus. November 1951. 
33p. diagrs., tab. (NACA RM L51H30) 

INVESTIGATION OF THE DISTRIBUTION OF UFT, 
DRAG, AND PITCHING MOMENT BETWEEN THE 
WING AND FUSELAGE OF A 1/30-SCALE SEMI- 
SPAN MODEL OF THE BELL X-5 AIRPLANE AT A 
MACH NUMBER OF 1. 24 BY THE NACA WDJG- 
FLOW METHOD. Norman S. Silsby and Garland J. 
Morris. January 1952. 32p. diagrs. , photos. , 
tab. (NACA RM L51K27) 

THE EFFECTIVENESS OF WING VORTEX GENER- 
ATORS IN IMPROVING THE MANEUVERING CHAR- 
ACTERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, George 
A. Rathert, Jr. and Richard S. Bray. February 1952. 
45p. photos., diagrs., tab. (NACA RM A51J18) 

LOW-SPEED STATIC LONGITUDINAL STABILITY 
AND CONTROL CHARACTERISTICS OF 60° 
TRIANGULAR -WING AND MODIFIED 60° 
TRIANGULAR-WING MODELS HAVING HALF- 
DELTA AND HALF-DLAMOND TIP CONTROLS. 
Jacob H. Lichtenstein and Byron M. Jaquet. 
February 1952. 36p. diagrs., photos., tab. (NACA 
RM L51K08) 

THE INTERFERENCE EFFECTS OF A BODY ON 
THE SPANWISE LOAD DISTRIBUTIONS OF TWO 
45° SWEPTBACK WINGS OF ASPECT RATIO 8 
FROM LOW -SPEED TESTS AT A REYNOLDS 
NUMBER OF 4 X 10^. Albert P. Martina. February 

1952. 48p. diagrs., photo., 2 tabs. (NACA 
RM L51K23) 

THE EFFECTS ON THE AERODYNAMIC CHARAC- 
TERISTICS OF VARYING THE WING THICKNESS 
RATIO OF A TRIANGULAR WING-BODY CONFIG- 
URATION AT TRANSONIC SPEEDS FROM TESTS BY 
THE NACA WING-FLOW METHOD. Albert W. Hall 
and James M. McKay. April 1952. 27p. diagrs., 
photo., 2 tabs. (NACA RM L52B18) 

SMALL-SCALE TRANSONIC INVESTIGATION OF 
THE EFFECTS OF PARTIAL-SPAN LEADING-EDGE 
CAMBER ON THE AERODYNAMIC CHARACTERIS- 
TICS OF A 50° 38' SWEPTBACK WING OF ASPECT 
RATIO 2.98. William J. Alford, Jr. and Andrew L. 
Byrnes, Jr. June 1952. 28p. diagrs., photo., tab. 
(NACA RM L52D08a) 

AN ANALYSIS OF ESTIMATED AND EXPERIMENT- 
AL TRANSONIC DOWNWASH CHARACTERISTICS 
AS AFFECTED BY PLAN FORM AND THICKNESS 
FOR WING AND WING-FUSELAGE CONFIGURA- 
TIONS. Joseph Weil, George S. Campbell and 
Margaret S. Dlederich. November 1952. 92p. 
diagrs. , 2 tabs. (NACA RM L52I22) 

CORRELATION OF BUFFET BOUNDARIES PRE- 
DICTED FROM WIND-TUNNEL TESTS WITH THOSE 
MEASURED DURING FLIGHT TESTS ON THE F8F-1 
AND X-1 AIRPLANES - TRANSONIC -BUMP METH- 
OD. Andrew Martin and James F. Reed. 
December 1952. 22p. diagrs., photos., tab. 
(NACA RM A52J17) 



AERODYNAMIC CHARACTERISTICS OF A REFINED 
DEEP-STEP PLANING-TAIL FLYING-BOAT HULL 
WITH VARIOUS FOREBODY AND AFTERBODY 
SHAPES. John M. Riebe and Rodger L. Naeseth. 
1953. ii, 19p. diagrs., photos., 8 tabs. (NACA 
Rept. 1144. Formerly TN 2489; RM L8F01) 

WING AND FUSELAGE LOADS MEASURED IN 
FLIGHT ON THE NORTH AMERICAN B-45 AND 
F-82 AIRPLANES. Paul W. Harper. February 
1953. 35p. diagrs., 4 tabs. (NACA RM L52L09) 

THEORETICAL INVESTIGATION OF THE EFFECTS 
UPON LIFT OF A GAP BETWEEN WING AND BODY 
OF A SLENDER WING-BODY COMBINATION. Duane 
W. Dugan and Katsumi Hikido. August 1954. 41p. 
diagrs. (NACA TN 3224) 

APPLICATION OF TWO-DIMENSIONAL VORTEX 
THEORY TO THE PREDICTION OF FLOW FIELDS 
BEHIND WINGS OF WING-BODY COMBINATIONS 
AT SUBSONIC AND SUPERSONIC SPEEDS. Arthur 
Wm. Rogers. September 1954. (ii), 91p. diagrs., 
photo., 3 tabs. (NACA TN 3227) 

INVESTIGATION OF LIFT, DRAG, AND PITCHING 
MOMENT OF A 60° DELTA -WING —BODY COM- 
BINATION (AGARD CALIBRATION MODEL B) IN 
THE LANGLEY 9-INCH SUPERSONIC TUNNEL. 
August F. Bromm, Jr. September 1954. 18p. 
diagrs., photos. (NACA TN 3300) 

ON THE DETERMINATION OF CERTAIN BASIC 
TYPES OF SUPERSONIC FLOW FIELDS. (Sulla 
determinazione di alcimi tlpi di campi di corrente 
ipersonora). Carlo Ferrari. November 1954. 17p. 
diagrs. (NACA TM 1381. Trans, from Rendiconti 
delta R. Accademie Nazionale del Lincei, Series 8, 
v. 7, no. 6, Dec. 1949) 

AERODYNAMIC FORCES, MOMENTS, AND STA- 
BILITY DERIVATIVES FOR SLENDER BODIES OF 
GENERAL CROSS SECTION. Alvin H. Sacks. 
November 1954. (i), 74p. diagrs., 2 tabs. (NACA 
TN 3283) 

DESCRIPTION AND ANALYSIS OF A ROCKET - 
VEHICLE EXPERIMENT ON FLUTTER INVOLVING 
WING DEFORMATION AND BODY MOTIONS. H. J. 
Cunningham and R. R. Lundstrom. January 1955. 
26p. diagrs., photos., 2 tabs. (NACA TN 3311. 
Formerly RM L50I29) 

ON THE CALCULATION OF THE 1-P OSCILLATING 
AERODYNAMIC LOADS ON SINGLE -ROTATION 
PROPELLERS IN PITCH ON TRACTOR AIRPLANES. 
Vernon L. Rogallo and Paul F. Yaggy. May 1955. 
28p. diagrs., photo. (NACA TN 3395) 



Wing-Nacelle 
(1.7. 1.1.2) 



WIND-TUNNEL INVESTIGATION OF A WING- 
FUSELAGE COMBINATION WITH EXTERNAL 
STORES. H. Norman Silvers and Kenneth P. 
Spreemann. July 9, 1948. 55p. diagrs. (NACA 
RM L7K20) 

AN ANALYSIS OF AVAILABLE DATA ON EFFECTS 
OF WING-FUSELAGE-TAIL AND WING-NACELLE 
INTERFERENCE ON THE DISTRIBUTION OF THE 
AIR LOAD AMONG COMPONENTS OF AIRPLANES. 
Bertram C. Wollner. April 11, 1949. 33p. diagrs., 
tab. (NACA RM L9B10) 



AERODYNAMICS 
AIRCRAFT (1.7) 



71 



Wing-Nacelle - Airplanes (Cont. ) 



WING AND FUSELAGE LOADS MEASUHED DJ 
FLIGHT ON THE NORTH AMERICAN B-45 AND 
F-82 AIRPLANES. Paul W. Harper. February 
1953. 35p. dlagrs., 4 tabs. (NACA RM L52L09) 

SOME NOTES ON THE AERODYNAMIC LOADS 
ASSOCIATED WITH EXTERNAL-STORE 
INSTALLATIONS. H. Norman Silvers and Thomas 
C. O'Bryan. June 1953. 17p. dlagrs. (NACA 
RM L53E06a) 

ON THE CALCULATION OF THE 1- P OSCILLATING 
AERODYNAMIC LOADS ON SINGLE -ROTATION 
PROPELLERS IN PITCH ON TRACTOR AIRPLANES. 
Vernon L. Rogallo and Paul F. Yaggy. May 1955. 
28p. dlagrs., photo. (NACA TN 3395) 



Tail-Wing and Fuselage 
(1.7.1.1.3) 



DRAG OF A WING-BODY CONFIGURATION CON- 
SISTING OF A SWEPT-FORWARD TAPERED WING 
MOUNTED ON A BODY OF FINENESS RATIO 12 
MEASURED DURING FREE FALL AT TRANSONIC 
SPEEDS. Jim Rogers Thompson and Charles W. 
Mathews. March 13, 1947, 15p. dlagrs., photos. 
(NACA RM L6L24) 

LONGITUDINAL STABIUTY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
WITH A SWEPT -BACK TAIL FROM TESTS AT 
TRANSONIC SPEEDS BY THE NACA WING-FLOW 
METHOD. John A. Zalovcik and Richard H. Sawyer. 
March 28, 1947. 30p. diagrs., photos., tab. (NACA 
RM L6K21) 

HIGH-SPEED WIND-TUNNEL TESTS OF A MODEL 
PURSUIT AIRPLANE AND CORRELATION WITH 
FLIGHT-TEST RESULTS. Joseph W. Cleary and 
Lyle J. Gray. January 21, 1948. 56p. dlagrs., 
photos. (NACA RM A7I16) 

WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 1.53 OF AN AIRPLANE WITH A TRIANGU- 
LAR WING. Richard Scherrer and William R. 
Wimbrow. January 23, 1948. 74p. diagrs., 
photos., 2 tabs. (NACA RM A7J05) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE. BASIC LONGITUDINAL STABILITY OF 
THE D-558-1. John B. Wright. May 12, 1948. 19p. 
diagrs., tab. (NACA RM L7K24) 

CURRENT STATUS OF LONGITUDINAL STABILITY. 
Charles J. Donlan. May 24, 1948. 16p. diagrs. 
(NACA RM L8A28) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/78- 
SCALE MODEL OF THE LOCKHEED YP-80A AIR- 
PLANE. Robert N. Olson and Leslie F. Lawrence. 
May 28, 1948. 52p. diagrs. photos. (NACA RM 
A7L24) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE. LONGITUDINAL STABILITY AND CON- 
TROL OF THE D-558-1. John B. Wright. July 8, 
1948. 47p. diagrs., tab. (NACA RM L8C23) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
WITH A SWEPTBACK WING AND TAIL FROM 
TESTS AT TRANSONIC SPEEDS BY THE NACA 
WING-FLOW METHOD. Richard H. Sawyer and 
Lindsay J. Lina. July 23, 1948. 42p. diagrs., 
photos., tab. (NACA RM L8B19) 



LONGITUDINAL STABIUTY AND CONTROL 
CHARACTERISTICS OF A SEMISPAN MODEL OF A 
SUPERSONIC AIRPLANE CONFIGURATION AT 
TRANSONIC SPEEDS FROM TESTS BY THE NACA 
WING- FLOW METHOD. Norman S. Silsby and 
James M. McKay. November 8, 1948. 30p. 
dlagrs., photos., tab. (NACA RM L8G30) 

AN INVESTIGATION OF THE LOW -SPEED STATIC 
STABILITY CHARACTERISTICS OF COMPLETE 
MODELS HAVING SWEPTBACK AND SWEPT FOB- 
WARD WINGS. M. Leroy Spearman and Paul 
Comisarow. November 19, 1948. Sip. diagrs., tab. 
photos. (NACA RM L8H31) 

EFFECT OF WING SWEEP, TAPER, AND THICK- 
NESS RATIO ON THE TRANSONIC DRAG CHARAC- 
TERISTICS OF WING-BODY COMBINATIONS. Jim 
Rogers Thompson and Charles W. Mathews. 
December 31, 1948. 29p. diagrs., photos., 2 tabs. 
(NACA RM L8K01) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRA^BONIC-BUMP 
METHOD. Joseph Weil and Kenneth W. Goodson. 
February 24, 1949. 28p. diagrs., photo., tab. 
(NACA RM L9A21) 

AN ANALYSIS OF AVAILABLE DATA ON EFFECTS 
OF WING-FUSELAGE-TAIL AND WING-NACELLE 
INTERFERENCE ON THE DISTRIBUTION OF THE 
AIR LOAD AMONG COMPONENTS OF AIRPLANES. 
Bertram C. WoUner. April 11, 1949. 33p. diagrs., 
tab. (NACA RM L9B10) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER -CHORD LINE SWEPT BACK 35°, 
ASPECT RATIO 4, TAPER RATIO 0. 6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. William C. Sleeman, Jr. and Robert E. 
Becht. April 21, 1949. 29p. diagrs., photo., tab. 
(NACA RM L9B25) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 4, TAPER RATIO 0.3, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Boyd C. Myers, II and Thomas J. King, 
Jr. July 20, 1949. 28p. diagrs., photo., tab. 
(NACA RM L9E25) 

AERODYNAMIC CHARACTERISTICS OF A DELTA 
WING WITH LEADING EDGE SWEPT BACK 45°, 
ASPECT RATIO 4, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. William 
C. Sleeman, Jr. and Robert E. Becht. September 6, 
1949. 29p. diagrs., photo., tab. (NACA 
RM L9G22a) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 60°, 
ASPECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Thomas J. King, Jr. and Boyd C. Myers, 
n. September 6, 1949. 32p. diagrs., photos., tab. 
(NACA RM L9G27) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH UNSWEPT QUARTER -CHORD LINE, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A006 
AIRFOIL SECTION. TRANSONIC -BUMP METHOD. 
Kenneth W. Goodson and William D. Morrison, Jr. 
October 21, 1949. 32p. diagrs., photos., tab. 
(NACA RM L9H22) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Kenneth W. Goodson and Albert G. Few, 
Jr. November 1, 1949. 34p. diagrs., photos., tab. 
(NACA RM L9I08) 



72 



AERODYNAMICS 
AIRCRAFT (1.7) 



Tail-Wing and Fuselage - Airplanes 
(Cont. ) 

LOW -SPEED STATIC LATERAL STABILITY CHAR- 
ACTERISTICS OF A CANARD MODEL HAVING A 
60° TRIANGULAR WING A^^D HORIZONTAL TAIL. 
William R. Bates. November 23, 1949. 29p. 
diagrs., tab. (NACA RM L9J12) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER -CHORD LINE SWEPT BACK 35°, 
ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC-BUMP 
METHOD. William C. Sleeman, Jr. and William D. 
Morrison, Jr. December 12, 1949. 32p. diagrs., 
photos., tab. (NACA RM L9K10a) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER -CHORD LINE SWEPT BACK 60°, 
ASPECT RATIO 2, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Boyd C. Myers, II and Thomas J. King, 
Jr. February 24, 1950. 31p. diagrs., photos., tab. 
(NACA RM L50A12) 

AERODYNAMIC INVESTIGATION AT MACH NUM- 
BER 1.92 OF A RECTANGULAR WING AND TAIL 
AND BODY CONFIGURATION AND ITS COMPO- 
NENTS. Macon C. Ellis, Jr. and Carl E. Grlgsby. 
March 1, 1950. 96p. diagrs., photos., 4 tabs. 
(NACA RM L9L28a) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X -5 AIRPLANE 
MODEL. LONGITUDINAL STABILITY AND CON- 
TROL. William B. Kemp, Jr. Robert E. Becht and 
Albert G. Few, Jr. March 14, 1950. 51p. diagrs., 
photos. (NACA RM L9K08) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 
65A009 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Kenneth P. Spreemann, William D. 
Morrison, Jr. and Thomas B. Pasteur, Jr. April 6, 
1950. 33p. diagrs., photos., tab. (NACA 
RM L50B03a) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH UNSWEPT QUARTER-CHORD LINE, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A004 
AIRFOIL SECTION. TRANSONIC-BUMP METHOD. 
Boyd C. Myers, n and James W. Wiggins. May 8, 
1950. 31p. diagrs., photos., tab. (NACA 
RM L50C16) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LATERAL AND DIRECTIONAL STABILITY 
AND CONTROL. William B. Kemp, Jr. and Robert 
E. Becht. June 20, 1950. 97p. diagrs., photos. 
(NACARM L50C17a) 

SPIN AND RECOVERY CHARACTERISTICS OF A 
MODEL OF A FIGHTER TYPE OF AIRPLANE WITH- 
OUT A HORIZONTAL TAIL AND HAVING EITHER A 
SINGLE VERTICAL TAIL OR TWIN VERTICAL 
TAILS. Lawrence J. Gale and Norman E. 
Pumphrey. July 25, 1950. 23p. diagrs., photos., 
2 tabs. (NACA RM L50F19a) 

STABILITY CHARACTERISTICS AT LOW SPEED OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL WITH 
VARIOUS MODIFICATIONS TO THE BASIC MODEL 
CONFIGURATIONS. Robert E. Becht and Albert G. 
Few, Jr. August 16, 1950. 47p. diagrs., photo. 
(NACA RM L50F23) 



LOW-SPEED STATIC STABILITY CHARACTERIS- 
TICS OF A CANARD MODEL WITH A 45° SWEPT- 
BACK WING AND A 60° TRIANGULAR HORIZONTAL 
CONTROL SURFACE. John W. Draper. 
September 6, 1950. 43p. diagrs., photo., 2 tabs. 
(NACA RM L50G11) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AT HIGH-SUBSONIC SPEEDS OF TWO 
MODELS OF A TRANSONIC RESEARCH AIRPLANE 
WITH WINGS AND HORIZONTAL TAILS OF ASPECT 
RATIOS 4.2 AND 2. Arvo A. Luoma and John B. 
Wright. September 29, 1950. 134p. diagrs., photos., 
Stabs. (NACA RM L50H07) 

LONGITUDINAL CHARACTERBTICS AT MACH 
NUMBER OF 1.24 OF 1/30-SCALE SEMISPAN 
MODEL OF BELL X-5 VARIABLE -SWEEP AIR- 
PLANE WITH WING SWEPT BACK 60° FROM TESTS 
BY NACA WING-FLOW METHOD. Norman S. 
Silsby, Garland J. Morris and Robert M. Kennedy. 
October 12, 1950. 17p. diagrs., photos., tab. 
(NACA RM L50E02a) 

DAMPING IN YAW AND STATIC DIRECTIONAL 
STABILITY OF A CANARD AIRPLANE MODEL AND 
OF SEVERAL MODELS HAVING FUSELAGES OF 
RELATIVELY FLAT CROSS SECTION. Joseph L. 
Johnson. October 16, 1950. 20p. diagrs., tab. 
(NACA RM L50H30a) 

THE EFFECT OF SWEEPBACK ON THE LONGITU- 
DINAL CHARACTERISTICS AT A MACH NUMBER 
OF 1.24 OF A 1/30-SCALE SEMISPAN MODEL OF 
THE BELL X-5 AIRPLANE FROM TESTS BY THE 
NACA WING-FLOW METHOD. Garland J. Morris, 
Robert M. Kennedy and Norman S. Silsby. 
November 27, 1950. 22p. diagrs., photos., tab. 
(NACA RM L50I28) 

STABILITY AND CONTROL CHARACTERISTICS OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL IN 
THE LANDING CONFIGURATION. Robert E. Becht. 
December 18, 1950. 38p. diagrs., photos. (NACA 
RM L50J27) 

LONGITUDINAL-CONTROL EFFECTIVENESS AND 
DOWNWASH CHARACTERISTICS AT A MACH NUM- 
BER OF 1.24 OF A 1/30-SCALE SEMISPAN MODEL 
OF THE BELL X-5 AIRPLANE AS DETERMINED BY 
THE NACA WING-FLOW METHOD. Richard H. 
Sawyer, Robert M. Kennedy and Garland J. Morris. 
January 8, 1951. 37p. diagrs., photos., tab. 
(NACA RM L50K15) 

STATIC LONGITUDINAL STABILITY AND 
DYNAMIC CHARACTERISTICS AT HIGH ANGLES 
OF ATTACK AND AT LOW REYNOLDS NUMBERS 
OF A MODEL OF THE X-3 SUPERSONIC RESEARCH 
AIRPLANE. Sanger M. Burk, Jr. and Burton E. 
Hultz. February 6, 1951. 76p. diagrs., photos., 
4 tabs. (NACA RM L50L19) 

EFFECTS OF A FUSELAGE FLAP DIVE BRAKE ON 
THE AERODYNAMIC CHARACTERISTICS OF 1/30- 
SCALE SEMISPAN MODEL OF THE BELL X-5 
VARIABLE -SWEEP AIRPLANE AT A MACH NUM- 
BER 1.24 AS DETERMINED BY THE NACA WING- 
FLOW METHOD. Robert M. Kennedy. Februarys, 
1951. 15p. diagrs., photos., tab. (NACA 
RM LSOLlla) 

CONTRIBUTIONS OF WING, TAIL, AND FUSELAGE 
TO THE AERODYNAMIC CHARACTERISTICS OF A 
SEMISPAN MODEL OF A SUPERSONIC AIRPLANE 
CONFIGURATION AT TRANSONIC SPEEDS FROM 
TESTS BY THE NACA WING-FLOW METHOD. 
Norman S. Silsby and James M. McKay. July 1951. 
34p. diagrs., photos., tab. (NACA RM L51EQ1) 



AERODYNAMICS 
AIRCRAFT (1.7) 



73 



Tail -Wing and Fuselage - Airplanes 
(Cont. ) 



STATIC LATERAL STABILITY CHARACTERISTICS 
OF A 1/10-SCALE MODEL OF THE X-1 AIRPLANE 
AT HIGH SUBSONIC MACH NUMBERS. Richard E. 
Kuhn and James W. Wiggins. August 1951. 25p. 
diagrs., photos. (NACA RM LSlFOla) 

A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT -WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
Seth B. Anderson and Richard S. Bray. November 
1951. 33p. diagrs., photo., tab. 

EFFECTS OF HORIZONTAL-TAIL POSITION, AREA, 
AND ASPECT RATIO ON LOW-SPEED STATIC 
LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A 60° TRUNGULAR-WING 
MODEL HAVING VARIOUS TRIANGULAR-ALL- 
MOVABLE HORIZONTAL TAILS. Byron M. Jaquet. 
December 1951. 61p. diagrs., photo., tab. (NACA 
RM L51I06) 

INVESTIGATION OF THE DISTRIBUTION OF LIFT, 
DRAG, AND PITCHING MOMENT BETWEEN THE 
WING AND FUSELAGE OF A 1/30-SCALE SEMI- 
SPAN MODEL OF THE BELL X-5 AIRPLANE AT A 
MACH NUMBER OF I. 24 BY THE NACA WING- 
FLOW METHOD. Norman S. Silsby and Garland J. 
Morris. January 1952. 32p. diagrs. , photos. , 
tab. (NACA RM L51K27) 

EFFECT OF CURRENT DESIGN TRENDS ON AIR- 
PLANE SPINS AND RECOVERIES. Anshal I. 
Neihouse. January 1952. 6p. diagrs. (NACA RM 
L52A09) 

INVESTIGATION OF THE LOW -SPEED AERODY- 
NAMIC CHARACTERISTICS OF A VARIABLE- 
SWEEP AIRPLANE MODEL WITH A TWISTED AND 
CAMBERED WING. William B. Kemp, Jr., Robert 
E. Becht and Albert G. Few, Jr. February 1952. 
62p. diagrs., photos. (NACA RM L51K22) 

LOW -SPEED STABILITY CHARACTERISTICS OF A 
COMPLETE MODEL WITH A WING OF W PLAN 
FORM. Edward C. Polhamus and Robert E. Becht. 
April 1952. 27p. diagrs., photo., tab. (NACA 
RM L52A25) 

EFFECTS OF HORIZONTAL-TAIL POSITION AND 
ASPECT RATIO ON LOW -SPEED STATIC LONGI- 
TUDINAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF A 60° TRIANGULAR -WING MODEL HAV- 
ING TWIN TRIANGULAR ALL-MOVABLE TAILS. 
Byron M. Jaquet. May 1952. 45p. diagrs., photos. 
(NACA RM L52B25) 

AN INVESTIGATION OF THE LOW -SPEED LONGI- 
TUDINAL STABILITY CHARACTERISTICS OF A 
SWEPT -WING AIRPLANE MODEL WITH TWO MODI- 
FICATIONS TO THE WING-ROOT PLAN FORM. 
William B. Kemp, Jr. July 1952. 17p. diagrs., 
tab. (NACA RM L52E07) 

A STUDY OF THE USE OF VARIOUS HIGH-LIFT DE- 
VICES ON THE HORIZONTAL TAIL OF A CANARD 
AIRPLANE MODEL AS A MEANS OF INCREASING 
THE ALLOWABLE CENTER-OF-GRAVITY 
TRAVEL. Joseph L. Johnson, Jr. January 1953. 
25p. diagrs., 2 tabs. (NACA RM L52K18a) 

FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW -SPEED STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A MODEL HAVING A FUSELAGE 
OR RELATIVELY FLAT CROSS SECTION. John W. 
Paulson and Joseph L. Johnson, Jr. February 1953. 
30p. diagrs., photo., tab. (NACA RM L52L22) 



THE CALCULATION OF PRESSURE ON SLENDER 
AIRPLANES IN SUBSONIC AND SUPERSONIC FLOW. 
Max. A. Heaslet and Harvard Lomax. 1954. 11. 
lip. diagrs. (NACA Kept. 1185. Formerly TN 2900) 

APPLICATION OF TWO-DIMENSIONAL VORTEX 
THEORY TO THE PREDICTION OF FLOW FIELDS 
BEHIND WINGS OF WING-BODY COMBINATIONS 
AT SUBSONIC AND SUPERSONIC SPEEDS. Arthur 
Wm. Rogers. September 1954. (11), 91p. diagrs., 
photo., 3 tabs. (NACA TN 3227) 

PREDICTION OF DOWNWASH BEHIND SWEPT -WING 
AIRPLANES AT SUBSONIC SPEED. John DeYoTing 
and Walter H. Barling, Jr. January 1955. 104p. 
diagrs., 3 tabs. (NACA TN 3346) 

EFFECT OF LAG OF SIDEWASH ON THE 
VERTICAL-TAIL CONTRIBUTION TO OSCIL- 
LATORY DAMPING IN YAW OF AIRPLANE 
MODELS. Lewis R. Fisher and Herman S. 
Fletcher. January 1955. 38p. diagrs., photos. 
(NACA TN 3358) 



External Stores 
(1.7. 1,1.5) 



WIND-TUNNEL INVESTIGATION OF A WING- 
FUSELAGE COMBINATION WITH EXTERNAL 
STORES. H. Norman Silvers and Kenneth P. 
Spreemann. July 9, 1948. 55p. diagrs. (NACA 
RM L7K20) 

EFFECT OF AIRFOIL SECTION AND TIP TANKS 
ON THE AERODYNAMIC CHARACTERISTICS AT 
HIGH SUBSONIC SPEEDS OF AN UNSWEPT WING 
OF ASPECT RATIO 5. 16 AND TAPER RATIO 0.61. 
H. Norman Silvers and Kenneth P. Spreemann. 
December 1, 1949. 30p. diagrs., photos., 2 tabs. 
(NACA RM L9J04) 

THE EFFECT OF TIP TANKS ON THE ROLLING 
CHARACTERISTICS AT HIGH SUBSONIC MACH 
NUMBERS OF A WING HAVING AN ASPECT RATIO 
OF 3 WITH QUARTER-CHORD LINE SWEPT BACK 
35°. Richard E. Ruhn and Bc^d C. Myers, H. 
January 17, 1950. 27ti. diagrs., photo., 2 tabs. 
(NACA RM L9J19) 

THE EFFECTS OF CENTRALLY MOUNTED WING- 
TIP TANKS ON THE SUBSONIC AERODYNAMIC 
CHARACTERISTICS OF A WING OF ASPSPT RATIO 
10 WITH 35° OF SWEEPBACK. Bruce E. Tlnllng and 
W. Richard Kolk. February 21, 1951. 44p. diagrs., 
photos., 2 Ubs. (NACA RM A50K15) 

THE EFFECT OF MASS DISTRIBUTION ON THE 
LOW -SPEED DYNAMIC LATERAL STABILITY AND 
CONTROL CHARACTERISTICS OF A MODEL WITH 
A 60° TRIANGULAR WING, Joseph L. Johnson. 
March 9, 1951. 23p. diagrs., 2 tabs. (NACA 
RM L50K10) 

PRELIMINARY STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTERB- 
TICS OF THIN WINGS. A. Gerald Ralney. July 1952. 
33p. diagrs., photo., tab. (NACA RM L52D08) 

SOME NOTES ON THE AERODYNAMIC LOADS 
ASSOCIATED WITH EXTERNAL-STORE 
INSTALLATIONS. H. Norman Silvers and Thomas 
C. O'Bryan. June 1953. 17p. diagrs. (NACA 
RM L53E06a) 

SOME OBSERVATIONS ON STALL FLUTTER AND 
BUFFETING. A. Gerald Ralney. June 1953. lip. 
diagrs. (NACA RM L53E15) 



7A 



AERODYNAMICS 
AIRCRAFT (1.7) 



External Stores - Airplanes (Cont. ) 



REDUCTION OF HELICOPTER PARASITE DRAG. 
Robert D. Harrington. Augiist 1954. 8p. diagrs. 
(NACA TN 3234) 

ARRANGEMENT OF FUSIFORM BODIES TO RE- 
DUCE THE WAVE DRAG AT SUPERSONIC SPEEDS. 
Morris D. Friedman and Doris Cohen. November 
1954 23p. diagrs. (NACA TN 3345. Formerly 
RM A51X20) 

EFFECTIVE MOMENT OF INERTIA OF FLUID IN 
OFFSET, INCLINED, AND SWEPT-WING TANKS 
UNDERGOING PITCHING OSCILLATIONS. James 
R. Reese and John L. Sewall. January 1955. 27p. 
diagrs., 6 tabs. (NACA TN 3353) 



SPECIFIC AIRPLANES 
(1.7.1.2) 



FLIGHT-TEST MEASUREMENTS OF AILERON CON- 
TROL SURFACE BEHAVIOUR AT SUPERCRITICAL 
MACH NUMBERS. Harvey H. Brown, George A. 
Rathert, Jr. and Lawrence A. Clousing. April 23, 
1947. 26p. diagrs., photos., 2 tabs. (NACA 
RM A7A15) 

FORCE AND LONGITUDINAL CONTROL CHARAC- 
TERISTICS OF A 1/16 - SCALE MODEL OF THE 
BELL XS-1 TRANSONIC RESEARCH AIRPLANE AT 
HIGH MACH NUMBERS. Axel T. Mattson. May 21, 
1947. 32p. diagrs., photo., tab. (NACA RM L7A03) 

AN ANALYSIS OF LONGITUDINAL -CONTROL 
PROBLEMS ENCOUNTERED IN FLIGHT AT TRAN- 
SONIC SPEEDS WITH A JET-PROPELLED AIR- 
PLANE. Harvey H. Brown, L. Stewart Rolls and 
Lawrence A. Clousing. September 25, 1947. 56p. 
diagrs., photos., 3 tabs. (NACA RM A7G03) 

MEASUREMENTS OF THE WING AND TAIL LOADS 
DURING THE ACCEPTANCE TESTS OF BELL XS-1 
RESEARCH AIRPLANE. De E. Beeler and John P. 
Mayer. April 13, 1948. 25p. diagrs., photos., 2 
tabs. (NACA RM L7L12) 

GENERAL HANDLING-QUALITIES RESULTS 
OBTAINED DURING ACCEPTANCE FLIGHT TESTS 
OF THE BELL XS-1 AIRPLANE. Walter C. 
Williams, Charles M. Forsyth and Beverly P. 
Brown. April 19, 1948. 72p. diagrs., photos., tab. 
(NACA RM L8A09) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE. BASIC LONGITUDINAL STABIUTY OF 
THE D-558-1. John B. Wright. May 12, 1948. 19p. 
diagrs., tab. (NACa RM L7K24) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/78- 
SCALE MODEL OF THE LOCKHEED YP-80A AIR- 
PLANE. Robert N. Olson and Leslie F. Lawrence. 
May 28, 1948. 52p. diagrs., photos. (NACA RM 
A7L24) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE. D-558-1 SPEED-REDUCTION BRAKE 
AND SYMMETRICAL-PROFILE WING CHARACTER- 
ISTICS. John B. Wright. June 15, 1948. 22p. 
diagrs., tab. (NACA RM L8B06) 



FORCE, STATIC LONGITUDINAL STABTLITY, AND 
CONTROL CHARACTERISTICS OF A 1/16-SCALE 
MODEL OF THE BELL XS-1 TRANSONIC RE- 
SEARCH AIRPLANE AT HIOI MACH NUMBERS. 
Axel T. Mattson and Donald L. Loving, June 23, 
1948. 49p. diagrs., tab. (NACA RM L8A12) 

LIMITED MEASUREMENTS OF STATIC LONGI- 
TUDINAL STABILITY IN FUGHT OF DOUGLAS 
D-558-1 AIRPLANE (BUAERO NO. 37971). Walter 
C. Williams. June 24, 1948. lOp. diagrs., photos., 
tab. (NACARM L8E14) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RE^ARCH AIR- 
PLANE. LONGITUDINAL STABILITY AND CON- 
TROL OF THE D-558-1. John B. Wright. July 8, 
1948. 47p. diagrs., tab. (NACA RM L8C23) 

DETERMINATION BY THE FREE-FALL METHOD 
OF THE LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A 1/4-SCALE MODEL OF 
THE BELL XS-1 AIRPLANE AT TRANSONIC 
SPEEDS. James T. Matthews, Jr. and Charles W. 
Mathews. November 9, 1948. 19p. diagrs., 
photo., tab. (NACA RM L8G29a) 

THEORETICAL INVESTIGATION OF THE DYNAMIC 
LATERAL STABILITY CHARACTERISTICS OF 
DOUGLAS DESIGN NO. 39C, AN EARLY VERSION 
OF THE X-3 RESEARCH AIRPLANE. Charles V. 
Bennett. January 18, 1949. 39p. diagrs., 2 tabs. 
(NACARM L8L31) 

STABIUTY AND CONTROL DATA OBTAINED FROM 
FIRST FLIGHT OF X-4 AIRPLANE. Hubert M. 
Drake. February 7, 1949. lip. diagrs., photos., 
tab. (NACA RM L9A31) 

FUGHT MEASUREMENT OF THE STABIUTY 
CHARACTERISTICS OF THE DOUGLAS D-558-1 
AIRPLANE (BUAERO NO. 37971) IN SIDESUPS. 
Walter C. Williams. April 18, 1949. 23p. diagrs., 
photos. (NACA RM L8E14a) 

MEASUREMENT OF THE DYNAMIC LATERAL 
STABILITY OF THE DOUGLAS D-558-1 AIRPLANE 
(BUAERO NO. 37971) IN RUDDER KICKS AT A MACH 
NUMBER OF 0.72. Hubert M. Drake. May 31, 1949. 
lOp. diagrs., photos. (NACA RM L9D06a) 

MEASURED CHARACTERISTICS OF THE DOUGLAS 
D-558-1 AIRPLANE (BUAERO NO. 37971) IN TWO 
LANDINGS. Hubert M. Drake. June 3, 1949. 8p. 
diagrs., photos. (NACA RM L9D20a) 

MEASUREMENTS OF AILERON EFFECTIVENESS 
OF BELL X-1 AIRPLANE UP TO A MACH NUMBER 
OF 0.82. Hubert M. Drake. June 20, 1949. 7p. 
diagrs. (NACA RM L9D13) 

RESULTS OBTAINED FROM SECOND FLIGHT OF 
X-4 AIRPLANE (A.F. NO. 46-676). Walter C. 
WilUams. July 18, 1949. 13p. diagrs., photos., tab. 
(NACA RM L9F21) 

THE STATIC-PRESSURE ERROR OF WING AND 
FUSELAGE AIRSPEED INSTALLATIONS OF THE X-1 
AIRPLANES IN TRANSONIC FLIGHT. Harold R. 
Goodman and Roxanah B. yancey. July 22, 1949. 
20p. diagrs. (NACA RM L9G22) 

STABIUTY AND CONTROL DATA OBTAINED FROM 
FOURTH AND FIFTH FLIGHTS OF THE NORTHROP 
X-4 AIRPLANE (A.F. NO. 46-676). George M. 
Valentine. August 4, 1949. 22p. diagrs., photos., 
tab. (NACA RM L9G25a) 



AERODYNAMICS 
AIRCRAFT (1.7) 



75 



Specific Airplanes (Cont. ) 



RESULTS OBTAKED FROM THIRD FUGHT OF 
NORTHROP X-4 AIRPLANE (A.F. NO. 46-676). 
Walter C. Williams. September 9, 1949. 13p. 
diagrs., photos., tab. (NACA RM L9G20a) 

AN INVESTIGATION OF THE SPIN, RECOVERY, 
AND TUMBLING CHARACTERISTICS OF A 1/20- 
SCALE MODEL OF THE NORTHROP X-4 AIRPLANE. 
Lawrence J. Gale, Ira P. Jones, Jr. and Jack H. 
Wilson. January 4, 1950. 27p. diagrs., photos., 4 
tabs. (NACA RM L9K28) 

A STUDY OF THE DYNAMIC STABILITY OF THE 
BELL X-1 RESEARCH AIRPLANE. Edward C. 
Polhamus. January 10, 1950. 16p. diagrs., tab. 
(NACA RM L9K04a) 

RESULTS OBTAINED DURING FLIGHTS 1 TO 6 OF 
THE NORTHROP X-4 AIRPLANfes(A.F. NO. 46-677). 
James T. Matthews, Jr. January 12, 1950. 19p. 
diagrs., photos., tab. (NACA RM L9K22) 

STALL CHARACTERISTICS OBTAINED FROM 
FLIGHT 10 OF NORTHROP X-4 NO. 2 AIRPLANE 
(USAF NO. 46-677). Melvin Sadoff and Thomas R. 
Sisk. February 27, 1950. 25p. diagrs., photos., tab. 
(NACA RM A50A04) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LONGITUDINAL STABILITY AND CON- 
TROL. William B. Kemp, Jr. Robert E. Becht and 
Albert G. Few, Jr. March 14, 1950. 51p. diagrs., 
photos. (NACA RM L9K08) 

MAXIMUM-LIFT INVESTIGATION OF A 1/40-SCALE 
X-1 AIRPLANE WING AT MACH NUMBERS FROM 
0.6d TO 1.15. Thomas R. Turner. April 21, 1950. 
18p. diagrs. (NACA RM L50C28) 

THEORETICAL INVESTIGATION OF THE DYNAMIC 
LATERAL STABILITY CHARACTERISTICS OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE, STUDY 
41-B. Charles V. Bennett. April 27, 1950. 31p. 
diagrs., 3 tabs. (NACA RM L50B28) 

AERODYNAMIC AND LATERAL-CONTROL CHAR- 
ACTERISTICS OF A 1/28-SCALE MODEL OF THE 
BELL X-1 AIRPLANE WING-FUSELAGE COMBINA- 
TION. TRANSONIC -BUMP METHOD. Vernard E. 
Lockwood. May 5, 1950. 28p. diagrs., tab. (NACA 
RM L50C22) 

FLIGHT INVESTIGATION OF THE AILERON CHAR- 
ACTERISTICS OF THE DOUGLAS D-558-I AIR- 
PLANE (BUAERO NO. 37972) AT MACH NUMBERS 
BETWEEN 0.6 AND 0.89. Jim Rogers Thompson, 
William S. Roden and John M. Eggleston. May 26, 
1950. 23p. diagrs., photos., tab. (NACA 
RM L50D20) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LATERAL AND DIRECTIONAL STABILITY 
AND CONTROL. William B. Kemp, Jr. and Robert 
E. Becht. June 20, 1950. 97p. diagrs., photos. 
(NACA RM L50C17a) 

LONGITUDINAL-STABILITY CHARACTERISTICS OF 
THE NORTHROP X-4 AIRPLANE (USAF NO. 46-677). 
Melvin Sadoff and Thomas R. Sisk. June 29, 1950. 
24p. diagrs., photos., tab. (NACA RM A50D27) 

STABIUTY CHARACTERISTICS AT LOW SPEED OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL WITH 
VARIOUS MODIFICATIONS TO THE BASIC MODEL 
CONFIGURATIONS. Robert E. Becht and Albert G. 
Few, Jr. August 16, 1950. 47p. diagrs., photo. 
(NACA RM L50F23) 



LOW -SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AIRPLANE - LONGITUDINAL 
CHARACTERISTICS. Noel K. Delany and Nora-Lee 
F. Hayter. September 8, 1950. 80p. diagrs., 
photos., 2 tabs. (NACA RM A50G06) 

PRELIMINARY FLIGHT INVESTIGATION OF THE 
WING-DROPPING TENDENCY AND LATERAL- 
CONTROL CHARACTERISTICS OF A 35° SWEPT- 
WING AIRPLANE AT TRANSONIC MACH NUMBERS. 
George A. Rathert, Jr. , L. Stewart Rolls, Lee 
Winograd and George E. Cooper. September 11, 
1950. 14p. diagrs., photo., tab. (NACA RM A50H03) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AT HIGH-SUBSONIC SPEEDS OF TWO 
MODELS OF A TRANSONIC RESEARCH AIRPLANE 
WITH WINGS AND HORIZONTAL TAILS OF ASPECT 
RATIOS 4.2 AND 2. Arvo A. Luoma and John B. 
Wright. September 29, 1950. 134p. diagrs., photos., 
3 tabs. (NACA RM L50H07) 

LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBER OF 1.24 OF 1/30-SCALE SEMBPAN 
MODEL OF BELL X-5 VARIABLE -SWEEP AIR- 
PLANE WITH WING SWEPT BACK 60° FROM TESTS 
BY NACA WING-FLOW METHOD. Norman S. 
Silsby, Garland J. Morris and Robert M. Kennedy. 
October 12, 1950. 17p. diagrs., photos., tab. 
(NACA RM L50E02a) 

FLIGHT CALIBRATION OF FOUR AIRSPEED 
SYSTEMS ON A SWEPT -WING AIRPLANE AT 
MACH NUMBERS UP TO 1.04 BY THE NACA 
RADAR-PHOTOTHEODOLITE METHOD. Jim 
Rogers Thompson, Richard S. Bray and George E. 
Cooper. October 27, 1950. 41p. diagrs., photos., 
tab. (NACA RM A50H24) 

THE EFFECT OF SWEEPBACK ON THE LONGITU- 
DINAL CHARACTERISTICS AT A MACH NUMBER 
OF 1.24 OF A 1/30-SCALE SEMISPAN MODEL OF 
THE BELL X-5 AIRPLANE FROM TESTS BY THE 
NACA WING-FLOW METHOD. Garland J. Morris, 
Robert M. Kennedy and Norman S. Silsby. 
November 27, 1950. 22p. diagrs., photos., tab. 
(NACA RM L50I28) 

PRELIMINARY FLIGHT INVESTIGATION OF THE 
DYNAMIC LONGITUDINAL-STABILITY CHARAC- 
TERISTICS OF A 35° SWEPT-WING AIRPLANE. 
William C. Triplett and Rudolph D. Van Dyke, Jr. 
December 11, 1950. 26p. diagrs., photo., tab. 
(NACA RM A50J09a) 

EFFECTS ON THE LATERAL CBCILLATION OF 
FIXING THE RUDDER AND REFLEXING THE 
FLAPS ON TH^ BELL X-1 AIRPLANE. Hubert M. 
Drake. December 11, 1950. 14p. diagrs., photo. 
(NACA RM L50I05) 

SUMMARY REPORT OF RESULTS OBTAINED DUR- 
ING DEMONSTRATION TESTS OF THE NORTHROP 
X-4 AIRPLANES. Melvin Sadoff and Thomas R. 
Sisk. December 13, 1950. 46p. diagrs., photos., 
tab. (NACA RM A50I01) 

STABILITY AND CONTROL CHARACTERISTICS OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL IN 
THE LANDING CONFIGURATION. Robert E. Becht. 
December 18, 1950. 38p. diagrs., photos. (NACA 
RM L50J27) 

LONGITUDINAL-CONTROL EFFECTIVENESS AND 
DOWNWASH CHARACTERISTICS AT A MACH NUM- 
BER OF 1.24 OF A 1/30-SCALE SEMISPAN MODEL 
OF THE BELL X-5 AIRPLANE AS DETERMINED BY 
THE NACA WING-FLOW METHOD. Richard H. 
Sawyer, Robert M. Kennedy and Garland J. Morris. 
January 8, 1951. 37p. diagrs., photos., tab. 
(NACA RM L50K15) 



AERODYNAMICS 
76 AIRCRAFT (1.7) 



Specific Airplanes (Cont. ) 



EFFECTS ON THE SNAKING OSCILLATION OF THE 
BELL X-1 AIRPLANE OF A TRABLING-EDGE BULB 
ON THE RUDDEH. Hubert M. Drake and Harry P. 
Clagett. January 16, 1951. 14p. diagrs., photo. 
(NACA RM LSOKOla) 

STATIC LONGITUDINAL STABILITY AND 
DYNAMIC CHARACTERISTICS AT HIGH ANGLES 
OF ATTACK AND AT LOW REYNOLDS NUMBERS 
OF A MCOEL OF THE X-3 SUPERSONIC RESEARCH 
AIRPLANE. Sanger M. Burk, Jr. and Burton E. 
Hultz. February 6, 1951. Kp. diagrs., photos., 
4 tabs. (NACA RM L50L19) 

EFFECTS OF A FUSELAGE FLAP DIVE BRAKE ON 
THE AERODYNAMIC CHARACTERISTICS OF 1/30- 
SCALE SEMISPAN MODEL OF THE BELL X-5 
VARIABLE -SWEEP AIRPLANE AT A MACH NUM- 
BER 1.24 AS DETERMINED BY THE NACA WING- 
FLOW METHOD. Robert M. Kennedy. February 8, 
1951. 15p. diagrs., photos., tab. (NACA 
RM LSOLlla) 

LOW-SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AIRPLANE - LATERAL AND 
DIRECTIONAL CHARACTERISTICS. Noel K. Delany 
and Nora-Lee F. Hayter. March 16, 1951. 56p. 
diagrs., photos., tab. (RM A51A16) 

FLIGHT INVESTIGATION OF THE LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
THE DOUGLAS D-558-I AIRPLANE (BUAERO 
NO 37972) AT MACH NUMBERS UP TO 0.89. Melvin 
Sadoff, William S. Roden and John M. Eggleston. 
June 1951. 26p. diagrs., photos., tab. (NACA 
RM L51D1«) 

A COMPARISON OF THE MEASURED AND PRE- 
DICTED LATERAL OSCILLATORY CHARACTER- 
ISTICS OF A 35° SWEPT -WING FIGHTER AIR- 
PLANE. Walter E. McNeill and George E. Cooper. 
July 1951. 21p. diagrs., 3 tabs. (NACARMA51C28) 

BUFTETING-LOAD MEASUREMENTS ON A JET- 
POWERED BOMBER AIRPLANE WITH REFLEXED 
FLAPS. John A. See and William S. Aiken, Jr. 
August 1951. 28p. diagrs., 3 tabs. (NACA 
mA L51E24a) 

STATIC LATERAL STABILITY CHARACTERISTICS 
OF A 1/10-SCALE MODEL OF THE X-1 AIRPLANE 
AT HIGH SUBSONIC MACH NUMBERS. Richard E. 
Kuhn and James W. Wiggins. August 1951. 25p. 
diagrs., photos. (NACA RM LSlFOla) 

TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED IN 
FLIGHT ON THE WING OF THE D-558-I RESEARCH 
AIRPLANE THROUGH A MACH NUMBER RANGE 
OF 0.80 TO 0.89 AND THROUGHOUT THE 
NORMAL-FORCE-COEFFICIENT RANGE AT MACH 
NUMBERS OF 0.61, 0.70, 0.855, AND 0.88. Earl 
R. Keener and Rozalia M. Bandish. August 1951. 
43p. diagrs., photos., 7 tabs. (NACA RM L51F12) 

FLIGHT DETERMINATION OF THE EFFECTS OF 
WING VORTEX GENERATORS ON THE AERO- 
DYNAMIC CHARACTERISTICS OF THE DOUGLAS 
D-558-I AIRPLANE. De E. Beeler, Donald R. 
Bellman and John H. Griffith. August 14, 1951. 23p. 
diagrs., photos., tab. (NACA RM L51A23) 



LONGITUDINAL FREQUENCY-RESPONSE CHARAC- 
TERISTICS OF A 35° SWEPT -WING AIRPLANE AS 
DETERMINED FROM FUGHT MEASUREMENTS, 
INCLUDING A METHOD FOR THE EVALUATION OF 
TRANSFER FUNCTIONS. WlUiam C. Triplett and G. 
Allan Smith. September 1951. 45p. diagrs., photo. 
(NACA RM A51G27) 

MEASUREMENTS IN FUGHT OF THE LONGITUDI- 
NAL CHARACTERISTICS OF TWO JET AIRCRAFT, 
ONE WITH A DIVING TENDENCY AND THE OTHER 
WITH A CLIMBING TENDENCY AT HIGH MACH 
NUMBERS. Seth B. Anderson. October 1951. 18p. 
diagrs., photos., 2 tabs. (NACA RM A51E14> 

STABILITY AND CONTROL MEASUREMENTS OB- 
TAINED DURING US AF -NACA COOPERATIVE 
FLIGHT-TEST PROGRAM ON THE X-4 AIRPLANE 
(USAF NO. 46-677). Melvin Sadoff, Herman O. 
Ankenbruck and William O'Hare. October 1951. 38p. 
diagrs., photos., tab. (NACA RM A51H09) 

A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT -WING AIRPLANE IN 
MANEUVERING FUGHT AT TRANSONIC SPEEDS. 
Seth B. Anderson and Richard S. Bray. November 
1951. 33p. diagrs., photo., tab. (NACA RM A51I12) 

PRESSURE DISTRIBUTION AT LOW SPEED ON A 
1/4-SCALE BELL X-5 AIRPLANE MODEL. 
WiUiam B. Kemp, Jr. and Albert G. Few, Jr. 
December 1951. 86p. diagrs., photos. (NACA 
RM L51I25) 

THE UNSYMMETRICAL LOAD AND BENDING 
MOMENT ON THE HORIZONTAL TAIL OF A JET- 
POWERED BOMBER MEASURED IN SIDESLIPPPING 
FLIGHT. T. V. Cooney. January 1952. 19p. 
diagrs., tab. (NACA RM L51J24) 

INVESTIGATION OF THE DISTRIBUTION OF UFT, 
DRAG, AND PITCHING MOMENT BETWEEN THE 
WING AND FUSELAGE OF A 1/30-SCALE SEMI- 
SPAN MODEL OF THE BELL X-5 AIRPLANE AT A 
MACH NUMBER OF 1. 24 BY THE NACA WING- 
FLOW METHOD. Norman S. Silsby and Garland J. 
Morris. January 1952. 32p. diagrs. , photos. , 
tab. (NACA RM L51K27) 

THE EFFECTIVrENESS OF WING VORTEX GENER- 
ATORS IN IMPROVING THE MANEUVERING CHAR- 
ACTERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, George 
A. Rathert, Jr. and Richard S. Bray. February 1952. 
45p. photos., diagrs., tab. (NACA RM A51J18) 

FULL-SCALE WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF WDJG MODIFICATIONS AND 
HORIZONTAL-TAIL LOCATION ON THE LOW- 
SPEED STATIC LONGITUDINAL CHARACTERBTICS 
OF A 35° SWEPT-WING AIRPLANE. Ralph L. Maki. 
April 1952. 54p. diagrs., photos., 7 tabs. (NACA 
RM A52B05) 

LATERAL AND DIRECTIONAL DYNAMIC - 
RESPONSE CHARACTERISTICS OF A 35° SWEPT- 
WING AIRPLANE AS DETERMINED FROM FLIGHT 
MEASUREMENTS. William C. Triplett and 
Stuart C. Brown. December 1952. 62p. diagrs., 
photo., 3 tabs. (NACA RM A52I17) 

CORRELATION OF BUFFET BOUNDARIES PRE- 
DICTED FROM WIND-TUNNEL TESTS WITH THOSE 
MEASURED DURING FLIffilT TESTS ON THE F8F-1 
AND X-1 AIRPLANES - TRANSONIC -BUMP METH- 
OD. Andrew Martin and James F. Reed. 
December 1952. 22p. diagrs., photos., tab. 
(NACA RM A52J17) 



AERODYNAMICS 
AIRCRAFT (1.7) 



77 



Specific Airplanes (Cont. ) 



MEASUBEMENTS OF FLUCTUATING PRESSURES 
ON A 1/4-SCALE MODEL OF THE X-1 AIRFLANE 
WITH A 10-PERCENT -THICK WING IN THE 
LANGLEY 16-FOOT TRANSONIC TUNNEL. 
Louis W. Habel and Seymour Steinberg. January 
1953. 29d. diagrs., photos. (NACA RM L52J31) 

THE VERTICAL-TAIL LOADS MEASURED DURING 
A FLIGHT INVESTIGATION ON A JET -POWERED 
BOMBER AIRPLANE. T. V. Cooney. May 1953. 
32p. diagrs., photo. (NACA RM L52G21) 

STEADY PROPERLY-BANKED TURNS OF 
TURBOJET-PROPELLED AIRPLANES. (La Virata 
Corretta Stazionaria Degli Aeroplani Azionati da 
Turboreattori). Angelo Miele. March 1955. 33p. 
diagrs., tab. (NACA TM 1382. Trans, from Rivista 
Aeronautica, v.27, no.l, 1951, p.23-35) 



PERFORMANCE 
(1,7. 1.3) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/78- 
SCALE MODEL OF THE LOCKHEED YP-80A AIR- 
PLANE. Robert N. Olson and Leslie F. Lawrence. 
May 28, 1948. 52p. diagrs., photos. (NACA RM 
A7L24) 

MEASURED CHARACTERISTICS OF THE DOUGLAS 
D-558-1 AIRPLANE (BUAERO NO. 37971) IN TWO 
LANDINGS. Hubert M. Drake. June 3, 1949. 8p. 
diagrs., photos. (NACA RM L9D20a) 

THE EFFECTIVENESS OF WING VORTEX GENER- 
ATORS IN IMPROVING THE MANEUVERING CHAR- 
ACTERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, George 
A. Rathert, Jr. and Richard S. Bray. February 1952. 
45p. photos., diagrs., tab. (NACA RM A51J18) 

A METHOD FOR EVALUATING THE EFFECTS OF 
DRAG AND INLET PRESSURE RECOVERY ON 
PROPULSION-SYSTEM PERFORMANCE. Emit J. 
Kremzier. August 1954. 21p. diagrs. (NACA 
TN 3261) 

INVESTIGATION OF THE AERODYNAMIC CHARAC- 
TERBTICS OF A MODEL WING-PROPELLER COM- 
BINATION AND OF THE WING AND PROPELLER 
SEPARATELY AT ANGLES OF ATTACK UP TO 90°. 
JohnW. Draper and Richard E. Kuhn. November 
1954. 72p. diagrs., photos., tab. (NACA TN 3304) 

AN INVESTIGATION OF A WING-PROPELLER CON- 
FIGURATION EMPLOYING LARGE-CHORD PLAIN 
FLAPS AND LARGE -DIAMETER PROPELLERS FOR 
LOW -SPEED FUGHT AND VERTICAL TAKE-OFF. 
Richard E. Kuhn and John W. Draper. December 
1954. 94p. diagrs., photos. (NACA TN 3307) 

DESIGN CONSIDERATIONS FOR WINGS HAVING 
MINIMUM DRAG DUE TO LIFT. Warren A. Tucker. 
December 1954. 26p. diagrs. (NACA TN 3317) 

INVESTIGATION OF EFFECTIVENESS OF LARGE- 
CHORD SLOTTED FLAPS IN DEFLECTING 
PROPELLER SLIPSTREAMS DOWNWARD FOR 
VERTICAL TAKE-OFF AND LOW-SPEED FLIGHT. 
Richard E. Kuhn and John W. Draper. January 
1955. 42p. diagrs., photo., tab. (NACA TN 3364) 



MISSILES 
(1.7.2) 



A TORSIONAL STIFFNESS CRITERION FOR PRE- 
VENTING FLUTTER OF WINGS OF SUPERSONIC 
MISSILES. Bernard Budiansky, Jaseph N. Kotanchik 
and Patrick T. Chiarito. August 28, 1947. 14p. 
diagrs., tab. (NACA RM L7G02) 



RESULTS OF FLIGHT TESTS TO DETERMINE THE 
ZERO-LIFT DRAG CHARACTERISTICS OF A 60° 
DELTA WING WITH NACA 65-006 AIRFOIL SEC- 
TION AND VARIOUS DOUBLE -WEDGE SECTIONS 
AT MACH NUMBERS FROM 0.7 TO 1.6. Clement J. 
Welsh. August 11, 1950. 15p. diagrs., photo. 
(NACA RM L5DF01) 



DRAG INVESTIGATION OF SOME FIN CONFIGURA- 
TIONS FOR BOOSTER ROCKETS AT MACH NUM- 
BERS BETWEEN 0.5 AND 1.4. John C. McFall, Jr. 
November 21, 1950. 17p. diagrs., photos., tab. 
(NACA RM L50J12) 



WIND-TUNNEL INVESTIGATION AT MACH 
NUMBERS FROM 0.50 TO 1.29 OF AN UNSWEPT 
TAPERED WING OF ASPECT RATIO 2.67 WITH 
LEADING- AND TRAILING-EDGE FLAPS - 
TRAILING-EDGE FLAPS DEFLECTED. Louis S. 
Stivers, Jr. and Ale:iander W. Malick. 
December 13, 1950. 45p. diagrs., photo., 5 tabs. 
(NACA RM A50J09b) 

WIND-TUNNEL INVESTIGATION AT MACH NUM- 
BERS FROM 0.50 TO 1.29 OF AN UNSWEPT, 
TAPERED WING OF ASPECT RATIO 2.67 WITH 
LEADING- AND TRAIUNG-EDGE FLAPS - 
LEADING-EDGE FLAPS DEFLECTED. Louis S. 
Stivers, Jr. and Alexander W. MaUck. February 26, 
1951. 37p. dUgrs., photo., 5 tabs. (NACA 
RM A50K10) 

SKIN-TEMPERATURE TELEMETER FOR 
DETERMINING BOUNDARY-LAYER HEAT- 
TRANSFER COEFFICIENTS. Clifford L. Fricke 
and Francis B. Smith. March 15, 1951. 22p. 
diagrs. (NACA RM L50J17) 

A SUMMARY OF AVAILABLE KNOWLEDGE CON- 
CERNING SKIN FRICTION AND HEAT TRANSFER 
AND ITS APPLICATION TO THE DESIGN OF HIGH- 
SPEED MISSILES. Morris W. Rubesin, Charles B. 
Rumsey and Steven A. Varga. November 1951. 17p. 
diagrs. (NACA RM A51J25a) 

VARIATION OF LOCAL LIQUID-WATER CONCEN- 
TRATION ABOUT AN ELLIPSOID OF FINENESS 
RATIO 5 MOVING IN A DROPLET FIELD. Robert 
G. Dorsch and Rinaldo J. Brun. July 1954. 68p. 
diagrs., photos., 2 tabs. (NACA TN 3153) 

VARIATION OF LOCAL LIQUID-WATER CONCEN- 
TRATION ABOUT AN ELLIPSOID OF FINENESS 
RATIO 10 MOVING IN A DROPLET FIELD. Rinaldo 
J. Brun and Robert G. Dorsch. April 1955. 51p. 
diagrs., photo., tab. (NACA TN 3410) 



78 



AERODYNAMICS 
AIRCRAFT (1.7) 



COMPONENTS IN COMBINATION 
(1.7.2.1) 



EFFECT OF WING SWEEP, TAPER, AND THICK- 
NESS RATIO ON THE TRANSONIC DRAG CHARAC- 
TERISTICS OF WMG-BODY COMBINATIONS. Jim 
Rogers Thompson and Charles W. Mathews. 
December 31, 1948. 29p. diagrs., photos., 2 tabs. 
(NACA RM L8K01) 

A THEORETICAL INVESTIGATION OF THE INFLU- 
ENCE OF AUXILIARY DAMPING IN PITCH ON THE 
DYNAMIC CHARACTERISTICS OF A PROPORTION- 
ALLY CONTROLLED SUPERSONIC CANARD MIS- 
SILE CONFIGURATION. Walter C. Nelson and 
Anthony L. Passera. August 25, 1950. 46p. 
diagrs., photo., 3 tabs. (NACA RM L50F30) 

DRAG INVESTIGATION OF SOME FIN CONFIGURA- 
TIONS FOR BOOSTER ROCKETS AT MACH NUM- 
BERS BETWEEN 0.5 AND 1.4. John C. McFall, Jr. 
November 21, 1950. 17p. diagrs., photos., tab. 
(NACA RM L50J12) 

THEORETICAL im^ESTIGATION OF AN AUTO- 
MATIC CONTROL SYSTEM WITH PRIMARY SENSI- 
TIVITY TO NORMAL ACCELERATIONS AS USED 
TO CONTROL A SUPERSONIC CANARD MISSILE 
CONFIGURATION. Ernest C. Seaberg and Earl F. 
Smith. July 1951. 48p. diagrs., photo., 3 tabs. 
(NACA RM L51D23) 

SYSTEM ANALYSES AND AUTOPILOT DESIGN FOR 
AUTOMATIC ROLL STABIUZATION OF A SUPER- 
SONIC PILOTLESS AIRCRAFT. Jacob Zarovsky. 
July 1951. 55p. diagrs., tab. (NACA RM L51E07) 

A THEORETICAL INVESTIGATION OF THE INFLU- 
ENCE OF AUTOPILOT NATURAL FREQUENCY 
UPON THE DYNAMIC PERFORMANCE CHARAC- 
TERISTICS OF A SUPERSONIC CANARD MISSILE 
CONFIGURATION WITH A PITCH-ATTITUDE CON- 
TROL SYSTEM. Anthony L. Passera. October 

1951. 32p. diagrs., photos., 2 tabs. (NACA 
RM L51H02) 

A THEORETICAL INVESTIGATION OF THE 
EFFECT OF A TARGET SEEKER SENSITIVE TO 
PITCH ATTITUDE ON THE DYNAMIC STABILITY 
AND RESPONSE CHARACTERISTICS OF A SUPER- 
SONIC CANARD MISSILE CONFIGURATION. 
Ordway B. Gates, Jr. and Albert A. Schy. August 

1952. 54p. diagrs., photo., tab. (NACA 
RM L52E19) 

THE EFFECT OF CONTROL-SURFACE-SERVO 
NATURAL FREQUENCY ON THE DYNAMIC PER- 
FORMANCE CHARACTERISTICS OF AN ACCELER- 
ATION CONTROL SYSTEM APPLIED TO A SUPER- 
SONIC MISSILE. Anthony L. Passera and Martin L. 
Nason. September 1953. 28p. diagrs., 3 tabs. 
(NACA RM L53G23a) 

FLIGHT MEASUREMENTS OF DRAG AND BASE 
PRESSURE OF A FIN-STABIUZED PARABOLIC 
BODY OF REVOLUTION (NACA RM-10) AT DIF- 
FERENT REYNOLDS NUMBERS AND AT MACH 
NUMBERS FROM 0.9 TO 3.3. H. Herbert Jackson, 
Charles B. Rumsey and Leo T. Chauvln. November 
1954. 20p. diagrs., photos. (NACA TN 3320. 
Formerly RM L50G24) 



Wing-Body 
(1.7.2.1.1) 



WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 1.53 OF AN AIRPLANE WITH A TRIANGU- 
LAR WING. Richard Scherrer and William R. 
Wimbrow. January 23, 1948. 74p. diagrs., 
photos., 2 tabs. (NACA RM A7J05) 

WIND-TUNNEL INVESTIGATION AT MACH NUM- 
BERS FROM 0.50 TO 1.20 OF AN ALL-MOVABLE 
TRLANGULAR WING OF ASPECT RATIO 4 ALONE 
AND WITH A BODY. Louis S. Stivers, Jr. and 
Alexander W. Mallck. February 2, 1950. -45?. 
diagrs., photos., tab. (NACA RM A9L01) 

FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.6 to 1.7 TO DETERMINE DRAG AND BASE 
PRESSURES ON A BLUNT -TRAILING-EDGE AIR- 
FOIL AND DRAG OF DIAMOND AND CIRCULAR- 
ARC AIRFOILS AT ZERO LIFT. John D. Morrow 
and Ellis Katz. August 11, 1950. 25p. diagrs., 
photos. (NACA RM L50E19a) 

MEASUREMENTS OF THE EFFECT OF TRAILING- 
EDGE THICKNESS ON THE ZERO-LIFT DRAG OF 
THIN LOW-ASPECT -RATIO WINGS. John D. 
Morrow. August 14, 19§0. 12p. diagrs., photo. 
(NACA RM L50F26) 

TRANSONIC DRAG CHARACTERISTICS OF A WING- 
BODY COMBINATION USING A THIN TAPERED 
WING OF 450 SWEEPBACK. Max C. Kurbjun and 
Stanley Faber. September 28, 1950. 14p. diagrs., 
photo., tab. (NACA RM L50H22) 

DRAG INVESTIGATION OF SOME FIN CONFIGURA- 
TUDNS for booster ROCKETS AT MACH NUM- 
BERS BETWEEN 0.5 AND 1.4. John C. McFall, Jr. 
November 21, 1950. 17p. diagrs., photos., tab. 
(NACA RM L50J12) 

NOTE ON FLUTTER OF A 60° DELTA WING 
ENCOUNTERED AT LOW-SUPERSONIC SPEEDS 
DURING THE FLIGHT OF A ROCKET-PROPELLED 
MODEL. William T. Lauten, Jr. and Grady L. 
Mitcham. May 14, 1951. 21p. diagrs., photos., 
5 tabs. (NACA RM L51B28) 

LOAD DISTRIBUTION OVER A FUSELAGE IN COM- 
BINATION WITH A SWEPT WING AT SMALL 
ANGLES OF ATTACK AND TRANSONIC SPEEDS. 
Maurice D. White and Bonne C. Look. November 
1951. 26p. diagrs., photo., tab. (NACA RM 
A51H15) 

INVESTIGATION OF LIFT AND CENTER OF PRES- 
SURE OF LOW -ASPECT-RATIO, CRUCIFORM, 
TRIANGULAR, AND RECTANGULAR WINGS IN 
COMBINATION WITH A SLENDER FUSELAGE AT 
HIGH SUPERSONIC SPEEDS. Thomas N. Canning 
and Billy Pat Denardo. June 1952. 28p. diagrs., 
photos. (NACA RM A52C24) 

THEORETICAL INVESTIGATION OF THE EFFECTS 
UPON LIFT OF A GAP BETWEEN WING AND BODY 
OF A SLENDER WING-BODY COMBINATION. Duane 
W. Dugan and Katsumi Hikido. August 1954. 41p. 
diagrs. (NACA TN 3224) 

APPLICATION OF TWO-DIMENSIONAL VORTEX 
THEORY TO THE PREDICTION OF FLOW FIELDS 
BEHIND WINGS OF WING-BODY COMBINATIONS 
AT SUBSONIC AND SUPERSONIC SPEEDS. Arthur 
Wm. Rogers. September 1954. (ii), 91p. diagrs., 
photo., 3 tabs. (NACA TN 3227) 



AERODYNAMICS 
AIRCRAFT (1.7) 



79 



Wing-Body - Missiles (Cont. ) 

AERODYNAMIC FORCES, MOMENTS, AND STA- 
BILITY DERIVATIVES FOR SLENDER BODIES OF 
GENERAL CROSS SECTION. Alvin H. Sacks. 
November 1954. (i), 74p. diagrs., 2 tabs. (NACA 
TN 3283) 

DESCRIPTION AND ANALYSIS OF A ROCKET - 
VEHICLE EXPERIMENT ON FLUTTER INVOLVING 
WING DEFORMATION AND BODY MOTIONS. H. J. 
Cunningham and R. R. Lundstrom. January 1955. 
26p. diagrs., photos., 2 tabs. (NACA TN 3311. 
Formerly RM L50I29) 



Tail -Body 
(1.7.2.1.2) 



FUGHT TESTS TO DETERMINE THE DRAG OF 
FIN-STABILIZED PARABOLIC BODIES AT TRAN- 
SONIC AND SUPERSONIC SPEEDS. Sidney R. 
Alexander, Leo T. Chauvin and Charles B. Rumsey. 
April 21, 1948. 24p. diagrs., photos. (NACA 
RM L8A05) 

DRAG MEASUREMENTS AT TRANSONIC SPEEDS 
OF TWO BODIES OF FINENESS RATIO 9 WITH 
DIFFERENT LOCATIONS OF MAXIMUM BODY 
DIAMETER. Jim Rogers Thompson and Max C. 
Kurbjun. July 22, 1948. 17p. diagrs., photos. 
(NACA RM L8A28b) 

TESTS OF LIFTING SURFACES ON CONICAL AND 
CYLINDRICAL PORTIONS OF A BODY AT SUBSONIC 
MACH NUMBERS AND AT A MACH NUMBER OF 1.2. 
Robert S. Osborne and John B. Wright. September 2, 
1949. 22p. diagrs. (NACA RM L9F29) 

MEASUREMENTS OF THE DRAG AND PRESSURE 
DISTRIBUTION ON A BODY OF REVOLUTION 
THROUGHOUT TRANSITION FROM SUBSONIC TO 
SUPERSONIC SPEEDS. Jim Rogers Thompson. 
January 16, 1950. 36p. diagrs., photos., 2 tabs. 
(NACA RM L9J27) 

RESULTS OF FLIGHT TESTS TO DETERMINE 
DRAG OF PARABOLIC AND CONE -CYLINDER 
BODIES OF VERY LARGE FINENESS RATIOS AT 
SUPERSONIC SPEEDS. Clement J. Welsh and 
Carlos A. deMoraes. August 1951. 17p. diagrs., 
photos. (NACA RM L51E18) 

PRELIMINARY INVESTIGATION OF THE DRAG 
CHARACTERISTICS OF THE NACA RM-10 MISSILE 
AT MACH NUMBERS OF 1.40 AND 1.59 IN THE 
LANGLEY 4- BY 4-FOOT SUPERSONIC TUNNEL. 
Lowell E. Hasel, Archibald R. Sinclair and Clyde V. 
Hamilton, April 1952. 49p. diagrs., photos, 3 tabs. 
(NACA RM L52A14) 

WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF VARIOUS DORSAL-FIN AND VERTICAL-TAIL 
CONFIGURATIONS ON THE DIRECTIONAL STABIL- 
ITY OF A STREAMLINED BODY OF TRANSONIC 
SPEEDS. TRANSONIC -BUMP METHOD. Harold S. 
Johnson and William C. Hayes. April 1953. 22p. 
diagrs., photo., tab. (NACA RM L53B19) 

SOME NEW DRAG DATA ON THE NACA RM-10 
MISSILE AND A CORRELATION OF THE EXISTING 
DRAG MEASUREMENTS AT M = 1.6 AND 3.0. 
Robert J. Garros and Carlton S. James. June 1954. 
24p. diagrs., photos., tab. (NACA TN 3171) 



APPLICATION OF TWO-DIMENSIONAL VORTEX 
THEORY TO THE PREDICTION OF FLOW FIELDS 
BEHIND WINGS OF WING-BODY COMBINATIONS 
AT SUBSONIC AND SUPERSONIC SPEEDS. Arthur 
Wm. Rogers. September 1954. (ii), 91p. diagrs., 
photo., 3 tabs. (NACA TN 3227) 



Jet Interference 
(1.7.2. 1.3) 



VELOCITY AND TEMPERATURE FIELDS IN CIR- 
CULAR.JET EXPANDING FROM CHOKED NOZZLE 
INTO QUIESCENT AIR. Morris D. Rousso and 
Fred D. Kochendorter. July 1951. 34p. diagrs., 
photos. (NACA RM E51F18. Formerly 
RM E50E03a) 



Wing-Tail-Body 
(1.7.2. 1.4) 



WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 1.53 OF AN AIRPLANE WITH A TRIANGU- 
LAR WING. Richard Scherrer and William R. 
Wimbrow. January 23, 1948. 74p. diagrs., 
photos., 2 tabs. (NACA RM A7J05) 

AERODYNAMIC INVESTIGATION AT MACH NUM- 
BER 1.92 OF A RECTANGULAR WING AND TAIL 
AND BODY CONFIGURATION AND ITS COMPO- 
NENTS. Macon C. Ellis, Jr. and Carl E. Grtgsby. 
March 1, 1950. 96p. diagrs., photob., 4 tabs. 
(NACA RM L9L28a) 

TRANSONIC DRAG CHARACTERISTICS OF A WING- 
BODY COMBINATION USING A THIN TAPERED 
WING OF 45° SWEEPBACK. Max C. Kurbjun and 
Stanley Faber. September 28, 1950. 14p. diagrs., 
photo., tab. (NACA RM L50H22) 

THE CALCULATION OF PRESSURE ON SLENDER 
AIRPLANES IN SUBSONIC AND SUPERSONIC FLOW. 
Max. A. Heaslet and Harvard Lomax. 1954. ii. 
lip. diagrs. (NACA Rept. 1185. Formerly TN 2900) 

APPLICATION OF TWO-DIMENSIONAL VORTEX 
THEORY TO THE PREDICTION OF FLOW FIELDS 
BEHIND WINGS OF WING-BODY COMBINATIONS 
AT SUBSONIC AND SUPERSONIC SPEEDS. Arthur 
Wm. Rogers. September 1954. (ii), 91p. diagrs., 
photo., 3 tabs. (NACA TN 3227) 



SPECIFIC MISSILES 
(1.7.2.2) 



OBSERVATIONS ON AN AILERON-FLUTTER IN- 
STABIUTY ENCOUNTERED ON A 45° SWEPT- 
BACK WING IN TRANSONIC AND SUPERSONIC 
FLIGHT. Marvin Pitkin, William N. Gardner and 
Howard J. Curfman, Jr. April 11, 1947. 23p. 
diagrs., photos. (NACA RM L6L09) 



AERODYNAMICS 
80 AIRCRAFT (1.7) 



Specific Missiles (Cont. ) 

THE PATH AND MOTION OF SCALE MODELS OF 
JETTISONABLE NOSE SECTIONS AT SUPERSONIC 
SPEEDS AS DETERMINED FROM AN INVESTIGA- 
TION IN THE LANGLEY FREE-FLIGHT APPARA- 
TUS. Lawrence J. Gale. May 23, 1950. 35p. 
diagrs., photos., 2 tabs. (NACA RM L9J13a) 

CORRELATION OF SUPERSONIC CONVECTIVE 
HEAT -TRANSFER COEFFICIENTS FROM MEAS- 
UREMENTS OF THE SKIN TEMPERATURE OF A 
PARABOLIC BODY OF REVOLUTION (NACA RM-10). 
Leo T. Chauvin and Carlos A. deMoraes. March 7, 
1951. 39p. diagrs., photo. 2 tabs. (NACA 
RM L51A18) 

AVERAGE SKIN-FRICTION COEFFICIENTS FROM 
BOUNDARY-LAYER MEASUREMENTS IN FLIGHT 
ON A PARABOLIC BODY OF REVOLUTION (NACA 
RM-10) AT SUPERSONIC SPEEDS AND AT LARGE 
REYNOLDS NUMBERS. Charles B. Rumsey and J. 
Dan Loposer. March 7, 1951. 33p. diagrs., photo. 
(NACA RM L51B12) 

PRELIMINARY INVESTIGATION OF THE DRAG 
CHARACTERISTICS OF THE NACA RM-10 MISSILE 
AT MACH NUMBERS OF 1.40 AND 1.59 IN THE 
LANGLEY 4- BY 4-FOOT SUPERSONIC TUNNEL. 
Lowell E. Hasel, Archibald R. Sinclair and Clyde V. 
Hamilton, April 1952. 49p. diagrs., photos, 3 tabs. 
(NACA RM L52A14) 

FLIGHT MEASUREMENTS OF THE EFFECTS OF 
SiraFACE CONDITION ON THE SUPERSONIC DRAG 
OF FIN-STABILIZED PARABOLIC BODIES OF REV- 
OLUTION. H. Herbert Jackson. May 1952. 17p. 
diagrs., photos. (NACA RM L52B26) 

FLIGHT MEASUREMENTS OF DRAG AND BASE 
PRESSURE OF A FIN-STABILIZED PARABOLIC 
BOBY OF REVOLUTION (NACA RM-10) AT DIF- 
FERENT REYNOLDS NUMBERS AND AT MACH 
NUMBERS FROM 0.9 TO 3.3. H. Herbert Jackson, 
Charles B. Rumsey and Leo T. Chauvin. November 
1954. 20p. diagrs., photos. (NACA TN 3320. 
Formerly RM L50G24) 



ROTATING -WING AIRCRAFT 
(1.7.3) 



COMPARISON OF HOVERING PERFORMANCE OF 
HELICOPTERS POWERED BY JET -PROPULSION 
AND RECIPROCATING ENGINES. Virginia L. 
Brightwell, Max D. Peters and J. C. Sanders. 
June 11, 1948. 39p. diagrs., 3 tabs. (NACA 
RM E7K21) 

RAPID ESTIMATION OF BENDING FREQUENCIES 
OF ROTATING BEAMS. Robert T. Yntema. 
August 1954. 18p. diagrs., tab. (NACA RM L54G05} 

REDUCTION OF HELICOPTER PARASITE DRAG. 
Robert D. Harrington. August 1954. 8p. diagrs. 
(NACA TN 3234) 

REVIEW OF INFORMATION ON INDUCED FLOW OF 
A LIFTING ROTOR. Alfred Gessow. August 1954. 
16p. diagrs., photo., tab. (NACA TN 3238) 



A METHOD FOR STUDYING THE TRANSIENT 
BLADE -FLAPPING BEHAVIOR OF LIFTING ROTORS 
AT EXTREME OPERATING CONDITIONS. Alfred 
Gessow and Aimer D. Crim. January 1955. 27p. 
diagrs. (NACA TN 3366) 



AUTOGIROS 
(1.7.3. 1) 



CHARTS FOR ESTIMATING PERFORMANCE OF 
HIGH-PERFORMANCE HEUCOPTERS. Alfred 
Gessow and Robert J. Tapscotti January 1955. 
36p. diagrs. (NACA TN 3323) 

A METHOD FOR STUDYING THE TRANSIENT 
BLADE -FLAPPING BEHAVIOR OF LIFTING ROTORS 
AT EXTREME OPERATING CONDITIONS. Alfred 
Gessow and Aimer D. Crim. January 1955. 27p. 
diagrs. (NACA TN 3366) 



HELICOPTERS 
(1.7.3.2) 



COMPARBON OF HOVERING PERFORMANCE OF 
HEUCOPTERS POWERED BY JET-PROPULSION 
AND RECIPROCATING ENGINES. Virginia L. 
Brightwell, Max D. Peters and J. C. Sanders. 
June 11, 1948. 39p. diagrs., 3 tabs. (NACA 
RM E7K21) 

STATIC DIRECTIONAL STABILITY OF A TANDEM- 
HELICOPTER FUSELAGE. Charles C. Smith, Jr. 
August 9, 1950. 23p. diagrs., photo. (NACA 
RM L50F29) 

DESCRIPTION AND INVESTIGATION OF A 
DYNAMIC MODEL OF THE XH-IT TWO-BLADE 
JET -DRIVEN HELICOPTER. George W. Brooks and 
Maurice A. Sylvester. March 14, 1951. 49p. 
diagrs., photos., 6 tabs. (NACA RM L50I21) 

PRELIMDJARY INVESTIGATION OF THE CONTROL 
OF A GAS-TURBINE ENGINE FOR A HELICOPTER. 
Richard P. Krebs. September 1951. 13p. diagrs. 
(NACA RM E51F19) 

SOME FLYING-QUALITIES STUDIES OF A TANDEM 
HELICOPTER. Kenneth B. Amer. October 1951. 
29p. diagrs., photos. (NACA RM L51H20a) 

FLIGHT TESTS OF A MAN STANDING ON A PLAT- 
FORM SUPPORTED BY A TEETERING ROTOR. 
Paul R. Hill and T. L. Kemiedy. March 1954. 26p. 
diagrs., photos. (NACA RM L54B12a) 

WIND-TUNNEL STUDIES OF THE PERFORMANCE 
OF MULTIROTOR CONFIGURATIONS. Richard C. 
Dingeldein. August 1954. lOp. diagrs., photo. 
(NACA TN 3236) 

HOVERING PERFORMANCE OF A HELICOPTER 
ROTOR USING NACA 8-H-12 AIRFOIL SECTIONS. 
Robert D. Powell, Jr. August 1954. 14p. diagrs., 
photos. (NACA TN 3237) 

SOME ASPECTS OF THE HEUCOPTER NOISE 
PROBLEM. Harvey H. Hubbard and Leslie W. 
Lassiter. August 1954. 14p. diagrs., photo. 
(NACA TN 3239) 



AERODYNAMICS 
AIRCRAFT (1.7) 



81 



Helicopters - Rotating -Wing 
Aircraft (Cont. ) 



PRELMINARY RESULTS FROM FLOW-FIELD 
MEASUREMENTS AROUND SINGLE AND TANDEM 
ROTORS IN THE LANGLEY FULL-SCALE TUNNEL. 
Harry H. Heyson. November 1954. 19p. diagrs., 
photos. (NACA TN 3242) 

INVESTIGATION OF THE AERODYNAMIC CHARAC- 
TERISTICS OF A MODEL WING-PROPELLER COM- 
BINATION AND OF THE WING AND PROPELLER 
SEPARATELY AT ANGLES OF ATTACK UP TO 90°. 
John W. Draper and Richard E. Kuhn. November 
1954. 72p. diagrs., photos., tab. (NACA TN 3304) 

AN INVESTIGATION OF A WING-PROPELLER CON- 
FIGURATION EMPLOYING LARGE-CHORD PLAIN 
FLAPS AND LARGE -DUMETER PROPELLERS FOR 
LOW-SPEED FUGHT AND VERTICAL TAKE-OFF. 
Richard E. Kuhn and John W. Draper. December 
1954. 94p. diagrs., photos. (NACA TN 3307) 

GUST EXPERIENCE OF A HELICOPTER AND AN 
AIRPLANE IN FORMATION FLIGHT. Aimer D. 
Crim. December 1954. 12p. diagrs., photos., 
2 tabs. (NACA TN 3354) 

CHARTS FOR ESTIMATING PERFORMANCE OF 
HIGH-PERFORMANCE HELICOPTERS. Alfred 
Gessow and Robert J. Tapscott. January 1955. 
36p. diagrs. (NACA TN 3323) 

INVESTIGATION OF EFFECTIVENESS OF LARGE- 
CHORD SLOTTED FLAPS IN DEFLECTING 
PROPELLER SLIPSTREAMS DOWNWARD FOR 
VERTICAL TAKE-OFF AND LOW -SPEED FLIGHT. 
Richard E. Kuhn and John W. Draper. January 
1955. 42p. diagrs., photo., tab. (NACA TN 3364) 

A METHOD FOR STUDYING THE TRANSIENT 
BLADE-FLAPPING BEHAVIOR OF LIFTING ROTORS 
AT EXTREME OPERATING CONDITIONS. Alfred 
Gessow and Aimer D. Crim. January 1955. 27p. 
diagrs. (NACA TN 3366) 

THE EFFECT OF CONTROL STIFFNESS AND FOR- 
WARD SPEED ON THE FLUTTER OF A 1/10-SCALE 
DYNAMIC MODEL OF A TWO-BLADE JET -DRIVEN 
HELICOPTER ROTOR. George W. Brooks and 
Maurice A. Sylvester. April 1955. 38p. diagrs., 
photo., 3 tabs. (NACA TN 3376) 



A STUDY OF NORMAL ACCELERATIONS AND 
OPERATING CONDITIONS EXPERIENCED BY 
HELICOPTERS IN COMMERCIAL AND MILITARY 
OPERATIONS. Marlin E. Hazen. April 1955. 34p. 
diagrs., photos., 5 tabs. (NACA TN 3434) 

A DYNAMIC -MODEL STUDY OF THE EFFECT OF 
ADDED WEIGHTS AND OTHER STRUCTURAL VAR- 
IATIONS ON THE BLADE BENDING STRAINS OF AN 
EXPERIMENTAL TWO-BLADE JET-DRIVEN HELI- 
COPTER IN HOVERING AND FORWARD FLIGHT. 
John Locke McCarty and George W. Brooks. May 
1955. i, 47p. diagrs., photo., 6 tabs. (NACA 
TN 3367) 



SEAPLANES 
(1.7.4) 



GENERAL STUDIES 
(1.7.4.1) 



PRELIMINARY WIND-TUNNEL INVESTIGATION AT 
HIGH -SUBSONIC SPEEDS OF PLANING-TAIL, 
BLENDED, AND AIRFOIL- FOREBODY SWEPT 
HULLS. John M. Riebe and Richard G. MacLeod. 
September 12, 1949. 33p. diagrs., photos., 3 tabs. 
(NACA RM L9D01) 



AERODYNAMIC CHARACTERISTICS OF A REFINED 
DEEP -STEP PLANING-TAIL FLYING-BOAT HULL 
WITH VARIOUS FOREBODY AND AFTERBODY 
SHAPES. John M. Riebe and Rodger L. Naeseth. 
1953. ii, 19p. diagrs., photos., 8 tabs. (NACA 
Rept. 1144. Formerly TN 2489; RM L8F01) 



THEORY AND PROCEDURE FOR DETERMINING 
LOADS AND MOTIONS IN CHINE -IMMERSED 
HYDRODYNAMIC IMPACTS OF PRISMATIC 
BODIES. Emanuel Schnitzer. 1953. ii, 29p. 
Srs. (NACA Rept. 1152. Formerly TN 2813) 



82 AERODYNAMICS 



Stability and Control 



(1.8) 



FLIGHT DETERMINATION OF THE EFFECTS OF 
WING VORTEX GENERATORS ON THE AERO- 
DYNAMIC CHARACTERISTICS OF THE DOUGLAS 
D-558-I AIRPLANE. De E. Beeler, Donald R. 
Bellman and John H. Griffith. August 14, 1951. 23p. 
dlagrs., photos., tab. (NACA RM L51A23) 

SOME FLYING-QUALITIES STUDIES OF A TANDEM 
HELICOPTER. Kenneth B. Amer. October 1951. 
29p. diagrs., photos. (NACA RM L51H20a) 

AN ANALYTICAL INVESTIGATION OF AIRPLANE 
SPIN-RECOVERY MOTION BY USE OF ROTARY- 
BALANCE AERODYNAMIC DATA. Stanley H. Scher. 
June 1954. 38p. diagrs., tab. (NACA TN 3188) 

STABILITY 
(l.S.l) 

STATIC 
(1.8.1.1) 

STABILITY AND CONTROL MEASUREMENTS OB- 
TAINED DURING USAF-NACA COOPERATIVE 
FLIGHT-TEST PROGRAM ON THE X-4 AIRPLANE 
(USAF NO. 46-677). Melvln Sadoff, Herman O. 
Ankenbruck and William O'Hare. October 1951. 38p. 
diagrs., photos., tab. (NACA RM A51H09) 

INVESTIGATION OF THE LOW -SPEED AERODY- 
NAMIC CHARACTERISTICS OF A VARIABLE - 
SWEEP AIRPLANE MODEL WITH A TWISTED AND 
CAMBERED WING. William B. Kemp, Jr., Robert 
E. Becht and Albert G. Fe«f Jr. February 1952. 
62p. diagrs., photos. (NACA RM L51K22) 

AERODYNAMIC FORCES, MOMENTS, AND STA- 
BILITY DERIVATIVES FOR SLENDER BODIES OF 
GENERAL CROSS SECTION. Alvin H. Sacks. 
November 1954.(1), 74p. diagrs., 2 tabs. (NACA 
TN 3283) 

Longitudinal 
(1.8. 1.1.1); 

LONGITUDINAL ST ABIUTY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
WITH A SWEPT -BACK TAIL FROM TESTS AT 
TRANSONIC SPEEDS BY THE NACA WING-FLOW 
METHOD. John A. Zalovcik and Richard H. Sawyer. 
March 28, 1947. 30p. diagrs., photos., tab. (NACA 
RM L6K21) 

HIGH-SPEED WIND-TUNNEL TESTS OF A MODEL 
PURSUIT AIRPLANE AND CORRELATION WITH 
FLIGHT -TEST RESULTS. Joseph W. Cleary and 
Lyle J. Gray. January 21, 1948. 5%). diagrs., 
photos. (NACA RM A7I16) 

WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 1.53 OF AN AIRPLANE WITH A TRIANGU- 
LAR WING. Richard Scherrer and William R. 
Wimbrow. January 23, 1948. 74p. diagrs., 
photos., 2 tabs. (NACA RM A7J05) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/78- 
SCALE MODEL OF THE LOCKHEED YP-80A AIR- 
PLANE. Robert N. Olson and Leslie F. Lawrence. 
May 28, 1948. 52p. diagrs., photos. (NACA RM 
A7L24) 

AN INVESTIGATION OF THE LOW -SPEED STATIC 
STABILITY CHARACTERISTICS OF COMPLETE 
MODELS HAVING SWEPTBACK AND SWEPT FOR- 
WARD WINGS. M. Leroy Spearman and Paul 
Comisarow. November 19, 1948. 51p. diagrs., tab. 
photos. (NACARM L8H31) 



STABILITY AND CONTROL DATA OBTAINED FROM 
FIRST FUGHT OF X-4 AIRPLANE. Hubert M. 
Drake. February 7, 1949. lip. diagrs., photos., 
tab. (NACA RM L9A31) 

AEI«)DYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Josq)h Weil and Kenneth W. Goodson. 
February 24, 1949. 28p. diagrs., photo., tab. 
(NACA RM L9A21) 

INVESTIGATION OF DOWNWAai AND WAKE CHAR- 
ACTERISTICS AT A MACH NUMBER OF 1.53. I - 
RECTANGULAR WING. Edward W. Perkins and 
Thomas N. Canning. March 1, 1949. 29p. diagrs. 
(NACA RM A8L16) 

FULL-SCALE INVESTIGATION OF A WING WITH 
THE LEADING EDGE SWEPT BACK 47. 5° AND 
HAVING CTRCULAR-ARC AND FINITE -TRAILING- 
EDGE -THICKNESS AILERONS. Roy H. Lange. 
March 11, 1949. 16p. diagrs., photo. (NACA 
RM L9B02) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER -CHORD LINE SWEPT BACK 35°, 
ASPECT RATIO 4, TAPER RATIO 0. 6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. William C. Sleeman, Jr. and Robert E. 
Becht. April 21, 1949. 29p. diagrs., photo., tab. 
(NACA RM L9B25) 

STABILITY RESULTS OBTAINED WITH DOUGLAS 
D-558-1 AIRPLANE (BUAERO NO. 37971) IN 
FLIGHT UP TO A MACH NUMBER OF 0.89. 
WUllam H. Barlow and Howard C. Lilly. April 22, 
1949. 16p. diagrs., photos. (NACA RM L8K03) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE. BASIC LONGITUDINAL STABILITY OF 
THE D-558-1. John B. Wright. May 12, 1948. 19p. 
diagrs., tab. (NACA RM L7K24) 

CURRENT STATUS OF LONGITUDINAL STABILITY. 
Charles J. Donlan. May 24, 1948. 16p. diagrs. 
(NACA RM L8A28) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE. D-558-1 SPEED-REDUCTION BRAKE 
AND SYMMETRICAL-PROFILE WING CHARACTER- 
ISTICS. John B. Wright. June 15, 1948. 22p. 
diagrs., tab. (NACA RM L8B06) 

FORCE, STATIC LONGITUDINAL STABILITY, AND 
CONTROL CHARACTERISTICS OF A 1/16-SCALE 
MODEL OF THE BELL XS-1 TRANSONIC RE- 
SEARCH AIRPLANE AT HIGH MACH NUMBERS. 
Axel T. Mattson and Donald L. Loving. June 23, 
1948. 49p. diagrs., tab. (NACA RM L8A12) 

LIMITED MEASUREMENTS OF STATIC LONGI- 
TUDINAL STABILITY IN FUGHT OF DOUGLAS 
D-558-1 AIRPLANE (BUAERO NO. 37971). Walter 
C. Williams. June 24, 1948. lOp. diagrs., photos., 
tab. (NACA RM L8E14) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE. LONGITUDINAL STABILITY AND CON- 
TROL OF THE D-558-1. John B. Wright. July 8, 
1948. 47p. diagrs., tab. (NACA RM L8C23) 



AERODYNAMICS 
STABILITY AND CONTROL (L. 8) 83 



Longitudinal Static Stability (Cont. ) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
AT TRANSONIC SPEEDS AS OBTAINED BY THE 
TRANSONIC -BUMP METHOD. Joseph Weil and 
M. Leroy Spearman. July 19, 1948. 23p. diagrs., 
tab. (NACA RM L8B03) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
WITH A SWEPTBACK WING AND TAIL FROM 
TESTS AT TRANSONIC SPEEDS BY THE NACA 
WING-FLOW METHOD. Richard H. Sawyer and 
Lindsay J. Lina. July 23, 1948. 42p. diagrs., 
photos., tab. (NACA RM L8B19) 

EFFECT OF DOWNWASH ON THE ESTIMATED 
ELEVATOR DEFLECTION REQUIRED FOR TRIM 
OF THE XS-1 AIRPLANE AT SUPERSONIC SPEEDS. 
James T. Matthews, Jr. November 1, 1948. lip. 
diagrs. (NACA RM L8H06a) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE - DYNAMIC PRESSURE AND COMPARISON 
OF POINT AND EFFECTIVE DOWNWASH AT THE 
TAIL OF THE D-558-1. Harold L. Robinson. 
November 4, 1948. 27p. diagrs. (NACA RM L8H05) 

LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A SEMISPAN MODEL OF A 
SUPERSONIC AIRPLANE CONFIGURATION AT 
TRANSONIC SPEEDS FROM TESTS BY THE NACA 
WING-FLOW METHOD. Norman S. Silsby and 
James M. McKay. November 8, 1948. 30p. 
diagrs., photos., tab. (NACA RM L8G30) 

DETERMINATION BY THE FREE-FALL METHOD 
OF THE LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A 1/4-SCALE MODEL OF 
THE BELL XS-1 AIRPLANE AT TRANSONIC 
SPEEDS. James T. Matthews, Jr. and Charles W. 
Mathews. November 9, 1948. 19p. diagrs., 
photo., tab. (NACA RM L8G29a) 

AERODYNAMIC CHARACTERISTICS AT SUBSONIC 
AND TRANSONIC SPEEDS OF A 42.7° SWEPTBACK 
WING MODEL HAVING AN AILERON WITH FINITE 
TRAILING-EDGE THICKNESS. Thomas R. Turner, 
Vernard E. Lockwood and Raymond 0. Vogler. 
January 12, 1949. 24p. diagrs., photo. (NACA 
RM L8K02) 

INVESTIGATION OF DOWNWASH AND WAKE CHAR- 
ACTERISTICS AT A MACH NUMBER OF 1.53. H - 
TRIANGULAR WING. Edward W. Perkins and 
Thomas N. Canning. June 6, 1949. 31p. diagrs. 
(NACA RM A9D20) 

RESULTS OBTAINED FROM SECOND FLIGHT OF 
X-4 AIRPLANE (A.F. NO. 46-676). Walter C. 
Williams. July 18, 1949. 13p. diagrs., photos., tab. 
(NACA RM L9F21) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 4, TAPER RATIO 0.3, AND NACA 
65A006 AIRFOILSECTION. TRANSONIC -BUMP 
METHOD. Boyd C. Myers, II and Thomas J. King, 
Jr. July 20, 1949. 28p. diagrs., photo., tab. 
(NACA RM L9E25) 

STABILITY AND CONTROL DATA OBTAINED FROM 
FOURTH AND FIFTH FLIGHTS OF THE NORTHROP 
X-4 AIRPLANE (A.F. NO. 46-876). George M. 
Valentine. August 4, 1949. 22p. diagrs., photos., 
tab. (NACA RM L9G25a) 



EFFECT OF SWEEPBACK ON THE LOW-SPEED 
STATIC AND ROLLING STABILITY DERIVATIVES 
OF THIN TAPERED WINGS OF ASPECT RATIO 4. 
William Letko and Walter D. Wolhart. August 9, 
1949. 36p. diagrs., photo. (NACA RM L9F14) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER- 
CHORD LINE SWEPT BACK 45°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. Raymond 
D. Vogler. August 15, 1949. 22p. diagrs. (NACA 
RM L9F29a) 

AERODYNAMIC CHARACTERISTICS OF A DELTA 
WING WITH LEADING EDGE SWEPT BACK 45°, 
ASPECT RATIO 4, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. William 
C. Sleeman, Jr. and Robert E. Becht. September 6, 
1949. 29p. diagrs., photo., tab. (NACA 
RM L9G22a) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 60°, 
ASPECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Thomas J. King, Jr. and Boyd C. Myers, 
II. September 6, 1949. 32p. diagrs., photos., tab. 
(NACA RM L9G27) 

RESULTS OBTAINED FROM THIRD FUGHT OF 
NORTHROP X-4 AIRPLANE (A.F. NO. 46-676). 
Walter C. Williams. September 9, 1949. 13p. 
diagrs., photos., tab. (NACA RM L9G20a) 

PRELIMINARY WIND-TUNNEL INVESTIGATION AT 
HIGH -SUBSONIC SPEEDS OF PLANING-TAIL, 
BLENDED, AND AIRFOIL-FOREBODY SWEPT 
HULLS. John M. Riebe and Richard G. MacLeod. 
September 12, 1949. 33p. diagrs., photos., 3 tabs. 
(NACA RM L9D01) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WtTH UNSWEPT QUARTER -CHORD LINE, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A006 
AIRFOIL SECTION. TRANSONIC -BUMP METHOD. 
Kenneth W. Goodson and William D. Morrison, Jr. 
October 21, 1949. 32p. diagrs., photos., tab. 
(NACA RM L9H22) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC-BUMP 
METHOD. Kenneth W. Goodson and Albert G. Few, 
Jr. November 1, 1949. 34p. diagrs., photos., tab. 
(NACA RM L9I08) 

DOWNWASH IN VORTEX REGION BEHIND 
TRAPEZOD3AL-WING TIP AT MACH NUMBER 1.91. 
J. L. Cummings, H. Mirels and L. E. Baughman. 
November 10, 1949. 39p. diagrs., photos. (NACA 
RM E9H15) 

EFFECT OF AIRFOIL SECTION AND TIP TANKS 
ON THE AERODYNAMIC CHARACTERISTICS AT 
HIGH SUBSONIC SPEEDS OF AN UNSWEPT WING 
OF ASPECT RATIO 5. 16 AND TAPER RATIO 0.61. 
H. Norman Silvers and Kenneth P. Spreemann. 
December 1, 1949. 30p. diagrs., photos., 2 tabs. 
(NACA RM L9J04) 

AERODYNAMIC CHARACTERBTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 35°, 
ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. William C. Sleeman, Jr. and William D. 
Morrison, Jr. December 12, 1949. 32p. diagrs., 
photos., tab. (NACA RM L9K10a) 



AERODYNAMICS 
84 STABILITY AND CONTROL (1.8) 



Longitudinal Static Stability (Cont. ) 

RESULTS OBTAINED DURING FLIGHTS 1 TO 6 OF 
THE NORTHROP X-4 AIRPLANE, (A. F. NO. 46-677). 
James T. Matthews, Jr. January 12, 1950. 19p. 
diagrs., photos., tab. (NACA RM L9K22) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER - 
CHORD LINE SWEPT BACK 35°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. Robert F. 
Thompson. January 25, 1950. 22p. diagrs., tab. 
(NACA RM L9L12a) 

MAXIMUM -LIFT INVESTIGATION AT MACH NUM- 
BERS FROM 0.05 TO 1.20 OF A WING WITH LEAD- 
ING EDGE SWEPT BACK 42°. Thomas R. Turner. 
February 14, 1950. 21p. diagrs. (NACA 
RM L9K03) 

SPDJ-TUNNEL INVESTIGATION OF A MODEL OF 
A 60° DELTA-WING AIRPLANE TO DETERMINE 
THE SPIN, RECOVERY, AND LONGITUDINAL 
TRIM CHARACTERISTICS THROUGHOUT AN 
EXTENSIVE RANGE OF MASS LOADINGS. Walter 
J. Kltnar and Ira P. Jones, Jr. February 15, 1950. 
56p. diagrs. , photos. , 6 charts, 4 tabs. 
(NACA RM L9L06) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 60°, 
ASPECT RATIO 2, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. TRANSONIC-BUMP 
METHOD. Boyd C. Myers, II and Thomas J. King, 
Jr. February 24, 1950. 31p. diagrs., photos., tab. 
(NACA RM L50A121 

STALL CHARACTERISTICS OBTAINED FROM 
FLIGHT 10 OF NORTHROP X-4 NO. 2 AIRPLANE 
(USAF NO. 46-677). Melvln SadoH and Thomas R. 
Sisk. February 27, 1950. 25p. diagrs., photos., tab. 
(NACA RM A50A04) 

AERODYNAMIC INVESTIGATION AT MACH NUM- 
BER 1.92 OF A RECTANGULAR WING AND TAIL 
AND BODY CONFIGURATION AND ITS COMPO- 
NENTS. Macon C. Ellis, Jr. and Carl E. Grlgsby. 
March 1, 1950. 96p. diagrs., photos,., 4 tabs. 
(NACA RM L9L28a) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER- 
CHORD LINE SWEPT BACK 60°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC-BUMP METHOD. Raymond 
D. Vogler. March 2, 1950. 21p. diagrs. (NACA 
RM L50A17) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH UNSWEPT QUARTER-CHORD LINE, ASPECT 
RATIO 2, TAPER RATIO 0.78, AND NACA 65A004 
AIRFOIL SECTION. TRANSONIC -BUMP METHOD. 
Edward C. Polhamus and George S. Campbell. 
March 8, 1950. 17p. diagrs., photos., tab. (NACA 
RM L50A18) 

EXPLORATORY INVESTIGATION OF LEADING- 
EDGE CHORD-EXTENSIONS TO IMPROVE THE 
LONGITUDINAL STABILITY CHARACTERISTICS OF 
TWO 52° SWEPTBACK WINGS. G. Chester Furlong. 
March 10, 1950. 32p. diagrs., photo. (NACA 
RM L50A30) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LONGITUDINAL STABILITY AND CON- 
TROL. William B. Kemp, Jr. Robert E. Becht and 
Albert G. Few, Jr. March 14, 1950. 51p. diagrs., 
photos. (NACA RM L9K08) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF A 
45° SWEPTBACK HORIZONTAL TAIL WITH PLAIN 
AND HORN-BALANCED CONTROL SURFACES. 
Harold S. Johnson and Robert F. Thompson. 
March 31, 1950. 44p. diagrs., photo., tab. (NACA 
RM L50B13) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH QUARTER-CHORD LINE SWEPT BACK 45°, 
ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 
65A009 AIRFOIL SECTION. TRANSONIC -BUMP 
METHOD. Kenneth P. Spreemann, William D. 
Morrison, Jr. and Thomas B. Pasteur, Jr. April 6, 
1950. 33p. diagrs., photos., tab. (NACA 
RM L50B03a) 

MAXIMUM-UFT INVESTIGATION OF A 1/40-SCALE 
X-1 AIRPLANE WING AT MACH NUMBERS FROM 
0.60 TO 1.15. Thomas R. Turner. AprU 21, 1950. 
18p. diagrs. (NACA RM L50C28) 

AERODYNAMIC CHARACTERISTICS WITH FIXED 
AND FREE TRANSITION OF A MODIFIED DELTA 
WING IN COMBINATION WITH A FUSELAGE AT 
HIGH SUBSONIC SPEEDS. Edward C. Polhamus and 
Thomas J. King, Jr. May 2, 1950. 19p. diagrs., 
photos. (NACA RM L50C21) 

AERODYNAMIC AND LATERAL-CONTROL CHAR- 
ACTERISTICS OF A 1/28-SCALE MODEL OF THE 
BELL X-1 AIRPLANE WING-FUSELAGE COMBINA- 
TION. TRANSONIC -BUMP METHOD. Vernard E. 
Lockwood. May 5, 1950. 28p. diagrs., tab. (NACA 
RM L50C22) 

AERODYNAMIC CHARACTERISTICS OF A WING 
WITH UNSWEPT QUARTER-CHORD LINE, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A004 
AIRFOIL SECTION. TRANSONIC -BUMP METHOD. 
Boyd C. Myers, II and James W. Wiggins. May 8, 
1950. 31p. diagrs., photos., tab. (NACA 
RM L50C16) 

WIND-TUNNEL INVESTIGATION AT LOW SPEED 
TO DETERMINE AERODYNAMIC PROPERTIES OF 
A JETTISONABLE NOSE SECTION WITH CIRCULAR 
CROSS SECTION. Roscoe H. Goodwin. May 19, 
1950. 38p. diagrs., photos. (NACA RM L9J13) 

LONGITUDINAL-STABILITY CHARACTERISTICS OF 
THE NORTHROP X-4 AIRPLANE (USAF NO. 46-677). 
Melvin Sadoff and Thomas R. Sisk. June 29, 1950. 
24p. diagrs., photos., tab. (NACA RM A50D27) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE AND SPOILER -TYPE CONTROLS ON A WING 
WITH QUARTER -CHORD-LINE SWEEPBACK OF 
60°, ASPECT RATIO 2, TAPER RATIO 0.6, AND 
NACA 65A006 AIRFOIL SECTION. TRANSONIC- 
BUMP METHOD. Alexander D. Hammond. July 18, 
1950. 26p. diagrs. (NACA RM L50E09) 

STABILITY CHARACTERISTICS AT LOW SPEED OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL WITH 
VARIOUS MODIFICATIONS TO THE BASIC MODEL 
CONFIGURATIONS. Robert E. Becht and Albert G. 
Few, Jr. August 16, 1950. 47p. diagrs., photo. 
(NACA RM L50F23) 

WING-FLOW MEASUREMENTS OF LONGITUDINAL 
STABILFTY AND CONTROL CHARACTERISTICS OF 
A CANARD AIRPLANE CONFIGURATION WITH A 
45° SWEPTBACK WING AND A TRIANGULAR ALL- 
MOVABLE CONTROL SURFACE. Harold L. Crane 
and James J. Adams. August 25, 1950. 53p. 
diagrs., photo. (NACA RM L50A3 1) 

LOW -SPEED STATIC STABILITY CHARACTERIS- 
TICS OF A CANARD MODEL WITH A 45° SWEPT- 
BACK WING AND A 60° TRIANGULAR HORIZONTAL 
CONTROL SURFACE. John W. Draper. 
September 6, 1950. 43p. diagrs., photo., 2 tabs. 
(NACARM L50G11) 



AERODYNAMICS 

STABILITY AND CONTROL, (1.8) 



85 



Longitudinal Static Stability (Cont. ) i 

LOW -SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AIRPLANE - LONGITUDINAL 
CHARACTERISTICS. Noel K. Delany and Nora-Lee 
F. Hayter. September 8, 1950. 80p. diagrs., 
photos., 2 tabs. (NACA RM A50G06) 

INVESTIGATION AT TRANSONIC SPEEDS OF A 
35-PERCENT-CHORD AILERON ON A TAPERED 
WEDGE-TYPE WING OF ASPECT RATIO 2.5 WITH 
AND WITHOirr A FUSELAGE. Thomas R. Turner 
and Joseph E. Fikes. September 8, 19S0. 25p. 
diagrs. (NACA RM L50G13a) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AT HIGH-SUBSONIC SPEEDS OF TWO 
MODELS OF A TRANSONIC RESEARCH AIRPLANE 
WITH WINGS AND HORIZONTAL TAILS OF ASPECT 
RATIOS 4.2 AND 2. Arvo A. Luoma and John B. 
Wright. September 29, 1950. 134p. diagrs., photos., 

3 tabs. (NACA RM L50H07) 

EFFECTS OF SWEEP ON THE MAXIMUM-LIFT 
CHARACTERBTICS OF FOUR ASPECT -RATIO-4 
WINGS AT TRANSONIC SPEEDS. Thomas R. Turner. 
October 3, 1950. 25p. diagrs. (NACA RM L50H11) 

AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBER OF 1.38 OF FOUR WiNGS OF ASPECT 
RATIO 4 HAVING QUARTER-CHORD SWEEP 
ANGLES OF 0°, 35°, 45°, AND 60°. WUUam B. 
Kemp, Jr., Kenneth W. Goodson and Robert A. Booth. 
October 10, 1950. 41p. diagrs., photos., tab. 
(NACA RM L50G14) 

LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBER OF 1.24 OF 1/30-SCALE SEMISPAN 
MODEL OF BELL X-5 VARIABLE-SWEEP AIR- 
PLANE WITH WING SWEPT BACK 60° FROM TESTS 
BY NACA WING-FLOW METHOD. Norman S. 
Silsby, Garland J. Morris and Robert M. Kennedy. 
October 12, 1950. 17p. diagrs., photos., tab. 
(NACA RM L50E02a) 

DOWNWASH IN VORTEX REGION BEHIND RECTAN- 
GULAR HALF -WING AT MACH NUMBER 1.91. John 
L. Cummings and Rudolph C. Haefeli. October 26, 
1950. 43p. diagrs., photos., tab. (NACA 
RM E50H10) 

THE EFFECT OF SWEEPBACK ON THE LONGITU- 
DINAL CHARACTERISTICS AT A MACH NUMBER 
OF 1.24 OF A 1/30-SCALE SEMISPAN MODEL OF 
THE BELL X-5 AIRPLANE FROM TESTS BY THE 
NACA WING-FLOW METHOD. Garland J. Morris, 
Robert M. Kennedy and Norman S. Silsby. 
November 27, 1950. 22p. diagrs., photos., tab. 
(NACA RM L50I28) 

LOW-SPEED INVESTIGATION OF THE EFFECT OF 
SEVERAL FLAP AND SPOILER AILERONS ON THE 
LATERAL CHARACTERISTICS OF A 47.5° 
SWEPTBACK-WING - FUSELAGE COMBINATION 
AT A REYNOLDS NUMBER OF 4.4 x lO^. Jerome 
Pasamanick and Thomas B. Sellers. December 8, 
1950. 57p. diagrs., photo. (NACA RM L50J20) 

PRELIMINARY FLIGHT INVESTIGATION OF THE 
DYNAMIC LONGITUDINAL -STABILITY CHARAC- 
TERISTICS OF A 35° SWEPT -WING AIRPLANE. 
William C. Triplett and Rudolph D. Van Dyke, Jr. 
December 11, 1950. 26p. diagrs., photo., tab. 
(NACA RM A50J09a) 

INVESTIGATION OF THE DOWNWASH AND WAKE 
BEHIND A TRIANGULAR WING OF ASPECT RATIO 

4 AT SUBSONIC AND SUPERSONIC MACH NIM- 
BERS. Harold J. Walker and Louis S. Stivers, Jr. 
December 12, 1950. 32p. diagrs. (NACA 

RM A50I14a) 



SUMMARY REPORT OF RESULTS OBTAINED DUR- 
ING DEMONSTRATION TESTS OF THE NORTHROP 
X-4 AIRPLANES. Melvin Sadoff and Thomas R. 
Sisk. December 13, 1950. 46p. diagrs., photos., 
tab. (NACA RM A5DI01) 

STABILITY AND CONTROL CHARACTERISTICS OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL IN 
THE LANDING CONFIGURATION. Robert E. Becht. 
December 18, 1950. 38p. diagrs., photos. (NACA 
RM L50J27) 

EFFECT OF AN END PLATE ON THE AERODY- 
NAMIC CHARACTERISTICS OF A 20.55° SWEPT- 
BACK WDJG WITH AN ASPECT RATIO OF 2.67 AND 
A TAPER RATIO OF 0.5. TRANSONIC -BUMP 
METHOD. Tames M. Watson, pecember 21, 1950. 
15p. diagrs., photo. (NACA RM L50H28a) 

LONGITUDINAL-CONTROL EFFECTIVENESS AND 
DOWNWASH CHARACTERISTICS AT A MACH NUM- 
BER OF 1.24 OF A 1/30-SCALE SEMISPAN MODEL 
OF THE BELL X-5 AIRPLANE AS DETERMINED BY 
THE NACA WING-FLOW METHOD. Richard H. 
Sawyer, Robert M. Kennedy and Garland J. Morris. 
January 8, 1951. 37p. diagrs., photos., tab. 
(NACA RM L50K15) 

STATIC LONGITUDINAL STABILITY AND 
DYNAMIC CHARACTERISTICS AT HIGH ANGLES 
OF ATTACK AND AT LOW REYNOLDS NUMBERS 
OF A MODEL OF THE X-3 SUPERSONIC RESEARCH 
AIRPLANE. Sanger M. Burk, Jr. and Burton E. 
Hultz. February 6, 1951. 76p. diagrs., photos., 
4 tabs. (NACA RM L50L19) 

EFFECTS OF A FUSELAGE FLAP DTVE BRAKE ON 
THE AERODYNAMIC CHARACTERISTICS OF 1/30- 
SCALE SEMISPAN MODEL OF THE BELL X-5 
VARIABLE -SWEEP AIRPLANE AT A MACH NUM- 
BER 1.24 AS DETERMINED BY THE NACA WING- 
FLOW METHOD. Robert M. Kennedy. February 8, 
1951. 15p. diagrs., photos., tab. (NACA 
RM LSOLlla) 

EXPERIMENTAL DOWNWASH AND WAKE CHAR- 
ACTERISTICS AT SUBSONIC AND SUPERSONIC 
MACH NUMBERS BEHIND AN UNSWEPT, TAPERED 
WING OF ASPECT RATIO 2.67 WITH LEADING- 
AND TRAILING-EDGE FLAPS. Harold J. Walker, 
Louis S. Stivers, Jr. and Luther Beard, Jr. 
April 20, 1951. 43p. diagrs. (NACA RM A51B16) 

EFFECT OF A DEFLECTABLE WING-TIP CON- 
TROL ON THE LOW -SPEED LATERAL AND 
LONGITUDINAL CHARACTERISTICS OF A LARGE- 
SCALE WING WITH THE LEADING EDGE SWEPT 
BACK 47.5°. Roy H. Lange and Marvin P. Fink. 
April 26, 1951. 41p. diagrs., photo., 2 tabs. 
(NACA RM L51C07) 

FLIGHT INVESTIGATION OF THE LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
THE DOUGLAS D-558-I AIRPLANE (BUAERO 
NO 37972) AT MACH NUMBERS UP TO 0.89. Melvin 
Sadoff, William S. Roden and John M. Eggleston. 
June 1951. 26p. diagrs., photos., tab. (NACA 
RM L51D1-8) 

AERODYNAMIC CHARACTERISTICS OF TAPERED 
WINGS HAVING ASPECT RATIOS OF 4, 6, AND 8, 
QUARTER-CHORD LINES SWEPT BACK 45°, AND 
NACA 631A012 AIRFOIL SECTIONS. TRANSONIC- 
BUMP METHOD. Edward C. Polhamus and 
Thomas J. King, Jr. June 13, 1951. 23p. diagrs., 
photos., 2 tabs. (NACA RM L51C26) 

EFFECTS OF SPANWISE THICKNESS VARIATION 
ON THE AERODYNAMIC CHARACTERISTICS OF 
35° AND 45° SWEPTBACK WINGS OF ASPECT 
RATIO 6. TRANSONIC -BUMP METHOD. WUUam 
D. Morrison, Jr. and Paul G. Fournier. July 1951. 
38p. diagrs., photo. (NACA RM L51D19) 



86 



AERODYNAMICS 

STABILITY AND CONTROL (I. 8) 



Longitudinal Static Stability (Cont. ) 

INVESTIGATION OF A TRIANGULAR WDJG IN CON- 
JUNCTION WITH A FUSELAGE AND HORIZONTAL 
TAIL TO DETERMINE DOWNWASH AND LONGITU- 
DINAL STABILITY CHARACTERISTICS - TRAN- 
SONIC BUMP METHOD. Edwin C. Allen. August 
1951. 22p. diagrs., photos. (NACA RM A51F12a) 

SMALL-SCALE INVESTIGATION AT TRANSONIC 
SPEEDS OF THE EFFECTS OF THICKENING THE 
INBOARD SECTION OF A 45° SWEPTBACK WING 
OF ASPECT RATIO 4, TAPER RATIO 0.3, AND 
NACA 65A006 AIRFOIL SECTION. Kenneth P. 
Spreemann and William J. Alford, Jr. August 1951. 
21p. diagrs., photo. (NACA RM L51F08a) 

A METHOD FOR THE DESIGN OF SWEPTBACK 
WINGS WARPED TO PRODUCE SPECIFIED FLIGHT 
CHARACTERISTICS AT SUPERSONIC SPEEDS. 
Warren A. Tucker. September 1951. 52p. diagrs., 
2 tabs. (NACA RM L51F08) 

MEASUREMENTS IN FLIGHT OF THE LONGITUDI- 
NAL CHARACTERISTICS OF TWO JET AIRCRAFT, 
ONE WITH A DIVING TENDENCY AND THE OTHER 
WITH A CLIMBING TENDENCY AT HIGH MACH 
NUMBERS. Beth B. Anderson. October 1951. 18p. 
diagrs., photos., 2 tabs. (NACA RM A51E14) 

A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT -WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
Beth B. Anderson and Richard S. Bray. November 
1951. 33p. diagrs., photo., tab. (NACA RM A51I12) 

AERODYNAMIC CHARACTERISTICS OF A 
LEADING-EDGE SLAT ON A 35° SWEPT -BACK 
WING FOR MACH NUMBERS FROM 0.30 TO 0.88. 
John ^. Kelly and Nora-Lee F. Hayter. December 
1951. 49p. diagrs., tab. (NACA RM A51H23) 

EFFECTS OF HORIZONTAL-TAIL POSITION, AREA, 
AND ASPECT RATIO ON LOW-SPEED STATIC 
LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A 60O TRIANGULAR-WING 
MODEL HAVING VARIOUS TRLANGULAR-ALL- 
MOVABLE HORIZONTAL TAILS. Byron M. Jaquet. 
December 1951. 61p. diagrs., photo., tab. (NACA 
RM L51I06) 

INVESTIGATION OF THE DISTRIBUTION OF UFT, 
DRAG, AND PITCHING MOMENT BETWEEN THE 
WING AND FUSELAGE OF A 1/30-SCALE SEMI- 
SPAN MODEL OF THE BELL X-5 AIRPLANE AT A 
MACH NUMBER OF 1. 24 BY THE NACA WING- 
FLOW METHOD. Norman S. Silsby and Garland J. 
Morris. January 1952. 32p. diagrs. , photos. , 
tab. (NACA RM L51K27) 

THE EFFECTIVENESS OF WING VORTEX GENER- 
ATORS IN IMPROVING THE MANEUVERING CHAR- 
ACTERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, George 
A. Rathert, Jr. and Richard S. Bray. February 1952. 
45p. photos., diagrs., tab. (NACA RM A51J18) 

LOW -SPEED STATIC LONGITUDINAL STABILITY 
AND CONTROL CHARACTERISTICS OF 60° 
TRIANGULAR-WING AND MODIFIED 60° 
TRIANGULAR-WING MODELS HAVING HALF- 
DELTA AND HALF-DIAMOND TIP CONTROLS. 
Jacob H. Lichtenstein and Byron M. Jaquet. 
February 1952. 36p. diagrs., photos., tab. (NACA 
RM L51K08) 

WIND-TUNNEL INVESTIGATION AT HIGH AND LOW 
SUBSONIC MACH NUMBERS OF A THIN SWEPT- 
BACK WING HAVING AN AIRFOIL SECTION DE- 
SIGNED FOR HIGH MAXIMUM LIFT. Stanley F. 
Racisz and Nicholas J. Paradiso. February 1952. 
46p. diagrs., photo., tab. (NACA RM L51L04) 



FULL-SCALE WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF WING MODIFICATIONS AND 
HORIZONTAL-TAIL LOCATION ON THE LOW- 
SPEED STATIC LONGITUDINAL CHARACTERISTICS 
OF A 35° SWEPT-WING AIRPLANE. Ralph L. Maki. 
April 1952. 54p. diagrs., photos., 7 tabs. (NACA 
RM A52B05) 

LOW-SPEED STABILITY CHARACTERISTICS OF A 
COMPLETE MODEL WITH A WING OF W PLAN 
FORM. Edward C. Polhamus and Robert E. Becht. 
April 1952. 27p. diagrs., photo., tab. (NACA 
RM L52A25) 

EFFECTS OF HORIZONTAL-TAIL POSITION AND 
ASPECT RATIO ON LOW -SPEED STATIC LONGI- • 
TUDINAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF A 60° TRIANGULAR -WING MODEL HAV- 
ING TWm TRIANGULAR ALL-MOVABLE TAILS. 
Byron M. Jaquet. May 1952. 45p. diagrs., photos. 
(NACA RM L52B25) 

AN INVESTIGATION OF LONGITUDINAL CONTROL 
CHARACTERISTICS OF A WING-TIP CONTROL 
SURFACE ON A SWEPTBACK WING AT TRANSONIC 
SPEEDS BY THE NACA WING-FLOW METHOD. 
James P. Trant, Jr. June 1952. 23p. diagrs., 
photos., tab. (NACA RM L52B15a) 

SMALL-SCALE TRANSONIC INVESTIGATION OF 
THE EFFECTS OF PARTIAL-SPAN LEADING-EDGE 
CAMBER ON THE AERODYNAMIC CHARACTERIS- 
TICS OF A 50° 38' SWEPTBACK WING OF ASPECT 
RATIO 2.98. William J. Alford, Jr. and Andrew L. 
Byrnes, Jr. June 1952. 28p. diagrs., photo., tab. 
(NACA RM L52D08a) 

AN INVESTIGATION OF THE LOW -SPEED LONGI- 
TUDINAL STABILITY CHARACTERISTICS OF A 
SWEPT-WING AIRPLANE MODEL WITH TWO MODI- 
FICATIONS TO THE WING-ROOT PLAN FORM. 
William B. Kemp, Jr. July 1952. 17p. diagrs., 
tab. (NACA RM L52E07) 

SMALL-SCALE TRANSONIC INVESTIGATION OF 
THE EFFECTS OF FULL-SPAN AND PARTIAL- 
SPAN LEADING-EDGE FLAPS ON THE AERO- 
DYNAMIC CHARACTERISTICS OF A 50° 3a' SWEPT- 
BACK WING OF ASPECT RATIO 2.98. Kenneth P. 
Spreemann and William J. Alford, Jr. July 1952. 
31p. diagrs., photo. (NACA RM L52E12) 

THE CALCULATION OF CERTAIN STATIC AERO- 
ELASTIC PHENOMENA OF WINGS WITH TIP 
TANKS OR BOOM-MOUNTED LIFTING SURFACES. 
Franklin W. Diederich and Kenneth A. Foss. 
August 1952. 55p. diagrs., 2 tabs. (NACA 
RM L52A22) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 60° DELTA WING EQUIPPED WITH A 
CONSTANT -CHORD FLAP-TYPE CONTROL WITH 
AND WITHOUT AN UNSHIELDED HORN BALANCE. 
TRANSONIC-BUMP METHOD. Harleth G. Wiley 
and Leon Zontek. September 1952. 25p. diagrs. 
(NACA RM L51H22) 

AN APPLICATION OF THE ROCKET-PROPELLED- 
MODEL TECHNIQUE TO THE INVESTIGATION OF 
LOW-LIFT BUFFETING AND THE RESULTS OF 
PRELIMINARY TESTS. Homer P. Mason and 
William N. Gardner. September 1952. 19p. 
diagrs., photos. (NACA RM L52C27) 

AN ANALYSIS OF ESTIMATED AND EXPERIMENT- 
AL TRANSONIC DOWNWASH CHARACTERBTICS 
AS AFFECTED BY PLAN FORM AND THICKNESS 
FOR WING AND WING-FUSELAGE CONHGURA- 
TIONS. Joseph Weil, George S. Campbell and 
Margaret S. Diederich. November 1952. 92p. 
diagrs. , 2 tabs. (NACA RM L52I22) 



AERODYNAMICS 
STABILITY AND CONTROL (1.8) 



87 



Longitudinal Static Stability (Cont. ) 

CORRELATION OF BUFFET BOUNDARIES PRE- 
DICTED FROM WIND-TUNNEL TESTS WITH THOSE 
MEASURED DURING FLIGHT TESTS ON THE F8F-1 
AND X-1 AIRPLANES - TRANSONIC-BUMP METH- 
OD. Andrew Martin and James F. Reed. 
December 1952. 22p. dlagrs., photos., tab. 
(NACA RM A52J17) 

CHARACTERISTICS OF FLAP-TYPE SPOILER 
AILERONS AT VARIOUS LOCATIONS ON A 60° 
DELTA WING WITH A DOUBLE SLOTTED FLAP. 
Delwin R. Croom. December 1952. 31p. dlagrs., 
3 tabs. (NACA RM L52J24) 

AERODYNAMIC CHARACTERISTICS OF A REFINED 
DEEP -STEP PLANING-TAIL FLYING-BOAT HULL 
WITH VARIOUS FOREBODY AND AFTERBODY 
SHAPES. John M. Riebe and Rodger L. Naeseth. 

1953. ii, 19p. dlagrs., photos., 8 tabs. (NACA 
Rept. 1144. Formerly TN 2489; RM L8F01) 

A STUDY OF THE USE OF VARIOUS HIGH-LIFT DE- 
VICES ON THE HORIZONTAL TAIL OF A CANARD 
AIRPLANE MODEL AS A MEANS OF INCREASING 
THE ALLOWABLE CENTER-OF-GRAVITY 
TRAVEL. Joseph L. Johnson, Jr. January 1953. 
25p. dlagrs., 2 tabs. (NACA RM L52K18a) 

FREE-FLIGHT-TUNNEL INVESTIGATION OF THE 
LOW -SPEED STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A MODEL HAVING A FUSELAGE 
OR RELATIVELY FLAT CROSS SECTION. John W. 
Paulson and Joseph L. Johnson, Jr. February 1953. 
30p. dlagrs., photo., tab. (NACA RM L52L22) 

INVESTIGATION OF THREE TAPERED 45° SWEPT- 
BACK CAMBERED AND TWISTED WINGS COVER- 
ING A SIMULTANEOUS VARIATION IN ASPECT 
RATIO AND THICKNESS RATIO AND OF ONE RE- 
LATED SYMMETRICAL WING AT TRANSONIC 
SPEEDS BY THE WING-FLOW METHOD. Harold I. 
Johnson. March 1953. 55p. dlagrs., photos., 2 tabs. 
(NACA RM L52H07) 

TRANSONIC AERODYNAMIC CHARACTERISTICS 
OF AN NACA 64AO06 AIRFOIL SECTION WITH A 
15-PERCENT-CHORD LEADING-EDGE FLAP. 
Milton D. Humphreys. September 1953. 44p. 
diagrs., photos. (NACA RM L53G23) 

INVESTIGATION OF LIFT, DRAG, AND PITCHING 
MOMENT OF A 60° DELTA-WING— BODY COM- 
BINATION (AGARD CALIBRATION MODEL B) IN 
THE LANGLEY 9-INCH SUPERSONIC TUNNEL. 
August F. Bromm, Jr. September 1954. 18p. 
dlagrs., photos. (NACA TN 3300) 

INVESTIGATION OF THE AERODYNAMIC CHARAC- 
TERISTICS OF A MODEL WING-PROPELLER COM- 
BINATION AND OF THE WING AND PROPELLER 
SEPARATELY AT ANGLES OF ATTACK UP TO 90°. 
John W. Draper and Richard E. Kuhn. November 

1954. 72p. dlagrs., photos., tab. (NACA TN 3304) 

AN INVESTIGATION OF A WING-PROPELLER CON- 
FIGURATION EMPLOYING LARGE -CHORD PLAIN 
FLAPS AND LARGE -DIAMETER PROPELLERS FOR 
LOW -SPEED FLIGHT AND VERTICAL TAKE-OFF. 
Richard E. Kuhn and John W. Draper. December 
1954. 94p. dlagrs., photos. (NACA TN 3307) 

PREDICTION OF DOWNWASH BEHIND SWEPT -WING 
AIRPLANES AT SUBSONIC SPEED. John DeYoung 
and Walter H. Barling, Jr. January 1955. 104p. 
dlagrs., 3 tabs. (NACA TN 3346) 



SOME EFFECTS OF PROPELLER OPERATION AND 
LOCATION ON ABILITY OF A WING WITH PLAIN 
FLAPS TO DEFLECT PROPELLER SLIPSTREAMS 
DOWNWARD FOR VERTICAL TAKE-OFF. John W. 
Draper and Richard E. Kuhn. January 1955. 28p. 
dlagrs., photo. (NACA TN 3360) 

INVESTIGATION OF EFFECTIVENESS OF LARGE - 
CHORD SLOTTED FLAPS IN DEFLECTING 
PROPELLER SLIPSTREAMS DOWNWARD FOR 
VERTICAL TAKE-OFF AND LOW -SPEED FLIGHT. 
Richard E. Kuhn and John W. Draper. January 
1955. 42p. dlagrs., photo., tob. (NACA TN 3364) 

STATIC STABILITY OF FUSELAGES HAVING A 
RELATIVELY FLAT CROSS SECTION. William R. 
Bates. March 1955. 29p. dlagrs., tab. (NACA 
TN 3429. Formerly RM L9I06a) 

Late ral 
(1.8. 1.1.2) 

FACTORS AFFECTING LATERAL STABILITY AND 
CONTROLLABILITY. John P. CampbeU and 
Thomas A. Toll. May 13, 1948. 19p. diagrs. 
(NACA RM L8A28a) 

AN INVESTIGATION OF THE LOW-SPEED STATIC 
STABILITY CHARACTERISTICS OF COMPLETE 
MODELS HAVING SWEPTBACK AND SWEPT FOR- 
WARD WINGS. M. Leroy Spearman and Paul 
Comisarow. November 19, 1948. 51p. dlagrs., tab. 
photos. (NACARM L8H31) 

THEORETICAL INVESTIGATION OF THE DYNAMIC 
LATERAL STABILITY CHARACTERISTICS OF 
DOUGLAS DESIGN NO. 39C, AN EARLY VERSION 
OF THE X-3 RESEARCH AIRPLANE. Charles V. 
Bennett. January 18, 1949. 39p. dlagrs., 2 tabs. 
(NACA RM L8L31) 

FLIGHT MEASUREMENT OF THE STABIUTY 
CHARACTERISTICS OF THE DOUGLAS D-558-1 
AIRPLANE (BUAERO NO. 37971) IN SIDESLIPS. 
Walter C. Williams. April 18, 1949. 23p. diagrs., 
photos. (NACA RM L8E 14a) 

STABILITY AND CONTROL DATA OBTAINED FROM 
FOURTH AND FIFTH FLIGHTS OF THE NORTHROP 
X-4 AIRPLANE (A.F. NO. 46-676). George M. 
Valentine. August 4, 1942. 22p. diagrs., photos., 
tab. (NACA RM L9G25a) 

EFFECT OF SWEEPBACK ON THE LOW -SPEED 
STATIC AND ROLUNG STABILITY DERIVATIVES 
OF THDJ TAPERED WINGS OF ASPECT RATIO 4. 
William Letko and Walter D. Wolhart. August 9, 
1949. 36p. dlagrs., photo. (NACA RM L9F14) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER - 
CHORD LINE SWEPT BACK 45°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. Raymond 
D. Vogler. August 15, 1949. 22p. diagrs. (NACA 
RM L9F29a) 

INVESTIGATION OF EXTENSIBLE WING-TIP 
AILERONS ON AN UNTAPERED SEMBPAN WING 
AT 0° AND 45° SWEEPBACK. John R. Hagerman 
and William M. O'Hare. September 20, 1949. 40p. 
dlagrs., photo., tab. (NACA RM L9H04) 

LOW -SPEED STATIC LATERAL STABILITY CHAR- 
ACTERISTICS OF A CANARD MODEL HAVING A 
60° TRIANGULAR WING AND HORIZONTAL TAIL. 
William R. Bates. November 23, 1949. 29p. 
diagrs., tab. (NACA RM L9J12) 



AERODYNAMICS 
88 STABILITY AND CONTROL (1.8) 



Lateral Static Stability (Cont. ) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER- 
CHORD LINE SWEPT BACK 35°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. Robert F. 
Thompson. January 25, 1950. 22p. diagrs., tab. 
(NACA RM L9L12a) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER- 
CHORD LINE SWEPT BACK 60°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC-BUMP METHOD. Raymond 

D. Vogler. March 2, 1950. 21p. diagrs. (NACA 
RM L50A17) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LATERAL AND DIRECTIONAL STABILITY 
AND CONTROL. William B. Kemp, Jr. and Robert 

E. Becht. June 20, 1950. 97p. diagrs., photos. 
(NACA RM L50C17a) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE AND SPOILER-TYPE CONTROLS ON A WDJG 
WITH QUARTER -CHORD-LINE SWEEPBACK OF 
60°, ASPECT RATIO 2, TAPER RATIO 0.6, AND 
NACA 65A006 AIRFOIL SECTION. TRANSONIC- 
BUMP METHOD. Alexander D. Hammond. July 18, 
1950. 26p. diagrs. (NACA RM L50E09) 

STABILITY CHARACTERISTICS AT LOW SPEED OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL WITH 
VARIOUS MODIFICATIONS TO THE BASIC MODEL 
CONFIGURATIONS. Robert E. Becht and Albert G. 
Few, Jr. August 16, 1950. 47p. diagrs., photo. 
(NACA RM L50F23) 

LOW-SPEED STATIC STABILITY CHARACTERIS- 
TICS OF A CANARD MODEL WITH A 45° SWEPT- 
BACK WING AND A 60° TRIANGULAR HORIZONTAL 
CONTROL SURFACE. John W. Draper. 
September 6, 1950. 43p. diagrs., photo., 2 tabs. 
(NACA RM L50GH) 

PRELIMINARY FLIGHT INVESTIGATION OF THE 
WING-DROPPING TENDENCY AND LATERAL- 
CONTROL CHARACTERISTICS OF A 35° SWEPT- 
WING AIRPLANE AT TRANSONIC MACH NUMBERS. 
George A. Rathert, Jr. , L. Stewart Rolls, Lee 
Winograd and George E. Cooper. September 11, 
1950. 14p. diagrs., photo., tab. (NACA RM A50H03) 

DAMPING IN YAW AND STATIC DIRECTIONAL 
STABILITY OF A CANARD AIRPLANE MODEL AND 
OF SEVERAL MODELS HAVING FUSELAGES OF 
RELATIVELY FLAT CROSS SECTION. Joseph L. 
Johnson. October 16, 1950. 20p. diagrs., tab. 
(NACA RM L50H30a) 

LOW -SPEED INVESTIGATION OF THE EFFECT OF 
SEVERAL FLAP AND SPOILER AILERONS ON THE 
LATERAL CHARACTERISTICS OF A 47.5° 
SWEPTBACK-WING - FUSELAGE COMBINATION 
AT A REYNOLDS NUMBER OF 4.4 x lO^. Jerome 
Pasamanick and Thomas B. Sellers. December 8, 
1950. 57p. diagrs., photo. (NACA RM L50J20) 

SUMMARY REPORT OF RESULTS OBTAINED DUR- 
ING DEMONSTRATION TESTS OF THE NORTHROP 
X-4 AIRPLANES. Melyln SadoH and Thomas R. 
Sisk. December 13, 1950. 46p. diagrs., photos., 
tab. (NACA RM A50I01) 

STABILITY AND CONTROL CHARACTERISTICS OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL IN 
THE LANDING CONFIGURATION. Robert E. Becht. 
December 18, 1950. 38p. diagrs., photos. (NACA 
RM L50J27) 



THE EFFECT OF MASS DISTRIBUTION ON THE 
LOW-SPEED DYNAMIC LATERAL STABIUTY AND 
CONTROL CHARACTERISTICS OF A MODEL WITH 
A 60° TRIANGULAR WDJG. Joseph L. Johnson. 
March 9, 1951. 23p. diagrs., 2 tabs. (NACA 
RM L50K10) 

LOW-SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AIRPLANE - LATERAL AND 
DIRECTIONAL CHARACTERISTICS. Noel K. Delany 
and Nora-Lee F. Hayter. March 16, 1951. 56p. 
diagrs., photos., tab. (RM A51A16) 

FUGHT MEASUREMENTS OF THE WING- 
DROPPING TENDENCY OF A STRAIGHT -WING JET 
AIRPLANE AT HIGH SUBSONIC MACH NUMBERS. 
Seth B. Anderson, Edward A. Ernst and Rudolph D. 
Van Dyke, Jr. April 24, 1951. 16p. diagrs., photo., 
tab. (NAGA RM A51B28) 

STATIC LATERAL STABILITY CHARACTERISTICS 
OF A 1/10-SCALE MODEL OF THE X-1 AIRPLANE 
AT HIGH SUBSONIC MACH NUMBERS. Richard E. 
Kuhn and James W. Wiggins. August 1951. 25p. 
diagrs., photos. (NACA RM L51F01a) 

THE EFFECTIVENESS OF WING VORTEX GENER- 
ATORS IN IMPROVING THE MANEUVERING CHAR- 
ACTERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, George 
A. Rathert, Jr. and Richard S. Bray. February 1952. 
45p. photos., diagrs., tab. (NACA RM A51J18) 

LOW-SPEED STABILITY CHARACTERISTICS OF A 
COMPLETE MODEL WITH A WING OF W PLAN 
FORM. Edward C. Polhamus and Robert E. Becht. 
April 1952. 27p. diagrs., photo., tab. (NACA 
RM L52A25) 

FLIGHT MEASUREMENTS OF THE LATERAL STA- 
BILITY AND CONTROL CHARACTERISTICS OF A 
HIGH-SPEED FIGHTER AIRPLANE. H. L. Crane, 
A. R. Beckhardt and C. E. Matheny. September 
1952. 50p. diagrs., tab. (NACA RM L52B14) 

AN APPLICATION OF THE ROCKET-PROPELLED- 
MODEL TECHNIQUE TO THE INVESTIGATION OF 
LOW-LIFT BUFFETING AND THE RESULTS OF 
PRELIMINARY TESTS. Homer P. Mason and 
William N. Gardner. September 1952. 19p. 
diagrs., photos. (NACA RM L52C27) 

A STUDY OF THE FLOW FIELD BEHIND THE TRI- 
ANGULAR HORIZONTAL TAIL OF A CANARD AIR- 
PLANE AT APPROXIMATELY THE VERTICAL- 
TAIL LOCATION BY MEANS OF A TUFT GRID. 
Joseph L. Johnson, Jr. October 1952. 18p. diagrs., 
tab. (NACA RM L52H11) 

LATERAL AND DIRECTIONAL DYNAMIC- 
RESPONSE CHARACTERISTICS OF A 35° SWEPT- 
WING AIRPLANE AS DETERMINED FROM FLIGHT 
MEASUREMENTS. William C. Triplett and 
Stuart C. Brown. December 1952. 62p. diagrs., 
photo., 3 tabs. (NACA RM A52I17) 

FREE-FUGHT -TUNNEL INVESTIGATION OF THE 
LOW-SPEED STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A MODEL HAVING A FUSELAGE 
OR RELATIVELY FLAT CROSS SECTION. JobnW. 
Paulson and Joseph L. Johnson, Jr. February 1953. 
30p. diagrs., photo., tab. (NACA RM L52L22) 

EFFECT OF HORIZONTAL-TAIL SPAN AND 
VERTICAL LOCATION ON THE AERODYNAMIC 
CHARACTERISTICS OF AN UNSWEPT TAIL 
ASSEMBLY IN SIDESLIP. Donald R. Riley. 1954. 
11, 20p. diagrs., photos., tab. (NACA Rept. 1171. 
Formerly TN 2907) 



AERODYNAMICS 
STABILITY AND CONTROL (1.8) 



89 



Lateral Static Stability (Cont. ) 

CAL.CULATED SUBSONIC SPAN LOADS AND 
RESULTING STABILITY DERIVATIVES OF UN- 
SWEPT AND 45° SWEPTBACK TAIL SURFACES IN 
SIDESLIP AND IN STEADY ROLL. M. 3. Queijo 
and Donald R. Riley. October 1954. llOp. 
diagrs., 2 tabs. (NACA TN 3245) 

STATIC STABILITY OF FUSELAGES HAVING A 
RELATIVELY FLAT CROSS SECTION. William R. 
Bates. March 1955. 29p. diagrs., tab. (NACA 
TN 3429. Formerly RM L9I06a) 

Directional 
{1.8, 1.1,3) 

WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 1.53 OF AN AIRPLANE WITH A TRIANGU- 
LAR WING. Richard Scherrer and William R. 
Wimbrow. January 23, 1948. 74p. diagrs., 
photos., 2 tabs. (NACA RM A7J05) 

FACTORS AFFECTING LATERAL STABILITY AND 
CONTROLLABILITY. John P. CampbeU and 
Thomas A. Toll. May 13, 1948. 19p. diagrs. 
(NACA RM L8A2Ba) 

AN INVESTIGATION OF THE LOW-SPEED STATIC 
STABILITY CHARACTERISTICS OF COMPLETE 
MODELS HAVING SWEPTBACK AND SWEPT FOR- 
WARD WINGS. M. Leroy Spearman and Paxil 
Comisarow. November 19, 1948. 51p. diagrs., tab. 
photos. (NACARM L8H31) 

FLIGHT MEASUREMENT OF THE STABILITY 
CHARACTERISTICS OF THE DOUGLAS D-558-1 
AIRPLANE (BUAERO NO. 37971) IN SIDESLIPS. 
Walter C. Williams. April 18, 1949. 23p. diagrs., 
photos. (NACA RM L8E14a) 

STABILITY AND CONTROL DATA OBTAINED FROM 
FOURTH AND FIFTH FLIGHTS OF THE NORTHROP 
X-4 AIRPLANE (A.F. NO. 46-676). George M. 
Valentine. August 4, 1949. 22p. diagrs., photos., 
tab. (NACA RM L9G25a) 

EFFECT OF SWEEPBACK ON THE LOW -SPEED 
STATIC AND ROLUNG STABILITY DERIVATIVES 
OF THIN TAPERED WINGS OF ASPECT RATIO 4. 
William Letko and Walter D. Wolhart. August 9, 

1949. 36p. diagrs., photo. (NACA RM L9F14) 

INVESTIGATION OF EXTENSIBLE WING-TIP 
AILERONS ON AN UNTAPERED SEMBPAN WING 
AT 0° AND 45° SWEEPBACK. John R. Hagerman 
and WlUiam M. O'Hare. September 20, 1949. 40p. 
diagrs., photo., tab. (NACA RM L9H04) 

LOW -SPEED STATIC LATERAL STABILITY CHAR- 
ACTERISTICS OF A CANARD MODEL HAVING A 
60° TRIANGULAR WING AND HORIZONTAL TAIL. 
William R. Bates. November 23, 1949. 29p. 
diagrs., tab. (NACA RM L9J12) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LATERAL AND DIRECTIONAL STABILITY 
AND CONTROL. William B. Kemp, Jr. and Robert 
E. Becht. June 20, 1950. 97p. diagrs., photos. 
(NACA RML50C 17a) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE AND SPOILER-TYPE CONTROLS ON A WING 
WITH QUARTER -CHORD-LINE SWEEPBACK OF 
60°, ASPECT RATIO 2, TAPER RATIO 0.6, AND 
NACA 65A006 AIRFOIL SECTION. TRANSONIC - 
BUMP METHOD. Alexander D. Hammond. July 18, 

1950. 26p. diagrs. (NACA RM L50E09) 



STATIC DIRECTIONAL STABILITY OF A TANDEM - 
HELICOPTER FUSELAGE. Charles C. Smith, Jr. 
August 9, 1950. 23p. diagrs., photo. (NACA 
RM L50F29) 

STABILITY CHARACTERISTICS AT LOW SPEED OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL WITH 
VARIOUS MODIFICATIONS TO THE BASIC MODEL 
CONFIGURATIONS. Robert E. Becht and Albert G. 
Few, Jr. Augtist 16, 1950. 47p. diagrs., photo. 
(NACA RM L50F23) 

LOW-SPEED STATIC STABILITY CHARACTERIS- 
TICS OF A CANARD MODEL WITH A 45° SWEPT- 
BACK WING AND A 60° TRIANGULAR HORIZONTAL 
CONTROL SURFACE. John W. Draper. 
September 6, 1950. 43p. diagrs., photo., 2 tabs. 
(NACA RM L50G11) 

DAMPING IN YAW AND STATIC DIRECTIONAL 
STABILITY OF A CANARD AIRPLANE MODEL AND 
OF SEVERAL MODELS HAVING FUSELAGES OF 
RELATIVELY FLAT CROSS SECTION. Joseph L. 
Johnson. October 16, 1950. 20p. diagrs., tab. 
(NACA RM L50H30a) 

LOW -SPEED INVESTIGATION OF THE EFFECT OF 
SEVERAL FLAP AND SPOILER AILERONS ON THE 
LATERAL CHARACTERISTICS OF A 47.5° 
SWEPTBACK-WING - FUSELAGE COMBINATION 
AT A REYNOLDS NUMBER OF 4.4 x 10^. Jerome 
Pasamanick and Thomas B. Sellers. December 8, 
1950. 57p. diagrs., photo. (NACA RM L50J20) 

STABILITY AND CONTROL CHARACTERISTICS OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL IN 
THE LANDING CONFIGURATION. Robert E. Becht. 
December 18, 1950. 38p. diagrs., photos. (NACA 
RM L50J27) 

LOW-SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AIRPLANE - LATERAL AND 
DIRECTIONAL CHARACTERISTICS. Noel K. Delany 
and Nora-Lee F. Hayter. March 16, 1951. 56p. 
diagrs., photos., tab. (RM A51A16) 

STATIC LATERAL STABILITY CHARACTERISTICS 
OF A 1/10-SCALE MODEL OF THE X-1 AIRPLANE 
AT HIGH SUBSONIC MACH NUMBERS. Richard E. 
Kuhn and James W. Wiggins. August 1951. 25p. 
diagrs., photos. (NACA RM L5 IFOla) 

LOW-SPEED STABILITY CHARACTERISTICS OF A 
COMPLETE MODEL WITH A WING OF W PLAN 
FORM. Edward C. Polhamus and Robert E. Becht. 
April 1952. 27p. diagrs., photo., tab. (NACA 
RM L52A25) 

FLIGHT MEASUREMENTS OF THE LATERAL STA- 
BILITY AND CONTROL CHARACTERISTICS OF A 
HIGH-SPEED FIGHTER AIRPLANE. H. L. Crane, 
A. R. Beckhardt and C. E. Matheny. September 
1952. 50p. diagrs., tab. (NACA RM L52B14) 

A STUDY OF THE FLOW FIELD BEHIND THE TRI- 
ANGULAR HORIZONTAL TAIL OF A CANARD AIR- 
PLANE AT APPROXIMATELY THE VERTICAL- 
TAIL LOCATION BY MEANS OF A TUFT GRID. 
Joseph L. Johnson, Jr. October 1952. 18p. diagrs., 
tab. (NACA RM L52H11) 

LATERAL AND DIRECTIONAL DYNAMIC - 
RESPONSE CHARACTERISTICS OF A 35° SWEPT- 
WING AIRPLANE AS DETERMINED FROM FLIGHT 
MEASUREMENTS. William C. Triplett and 
Stuart C. Brown. December 1952. 62p. diagrs., 
photo., 3 tabs. (NACA RM A52I17) 



AERODYNAMICS 
90 STABILITY AND CONTROL (1.8) 



Directional Static Stability (Cont. ) 

AERODYNAMIC CHARACTERISTICS OF A REFINED 
DEEP-STEP PLANING-TAIL FLYING-BOAT HULL 
WITH VARIOUS FOREBODY AND AFTERBODY 
SHAPES. John M. Riebe and Rodger L. Naeseth. 
1953. ii, 19p. diagrs,, photos., 8 tabs. (NACA 
Rept. 1144. Formerly TN 2489 RM L8F01) 

FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW -SPEED STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A MODEL HAVING A FUSELAGE 
OR RELATIVELY FLAT CROSS SECTION. John W. 
Paulson and Joseph L. Johnson, Jr. February 1953. 
30p. diagrs., photo., tab. (NACA RM L52L22) 

WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF VARIOIS DORSAL-FIN AND VERTICAL-TAIL 
CONFIGURATIONS ON THE DIRECTIONAL STABIL- 
ITY OF A STREAMLINED BODY OF TRANSONIC 
SPEEDS. TRANSONIC-BUMP METHOD. Harold S. 
Johnson and William C. Hayes. April 1953. 22p. 
diagrs., photo., tab. (NACA RM L53B19) 

EFFECT OF LAG OF SIDEWASH ON THE 
VERTICAL-TAIL CONTRIBUTION TO OSCIL- 
LATORY DAMPING IN YAW OF AIRPLANE 
MODELS. Lewis R. Fisher and Herman S. 
Fletcher. January 1955. 38p. diagrs., photos. 
(NACA TN 3356) 

STATIC STABILITY OF FUSELAGES HAVING A 
RELATIVELY FLAT CROSS SECTION. William R. 
Bates. March 1955. 29p. diagrs., tab. (NACA 
TN 3429. Formerly RM L9I06a) 

DYNAMIC 
(1.8.1.2) 

LABORATORY INVESTIGATION OF AN AUTOPILOT 
UTILIZING A MECHANICAL LINKAGE WITH A DEAD 
SPOT TO OBTAIN AN EFFECTIVE RATE SIGNAL. 
Ernest C. Seaberg. August 17, 1949. 29p. diagrs., 
photos., tab. (NACA RM L9F15a) 

A THEORETICAL INVESTIGATION OF THE INFLU- 
ENCE OF AUXILIARY DAMPING IN PITCH ON THE 
DYNAMIC CHARACTERISTICS OF A PROPORTION- 
ALLY CONTROLLED SUPERSONIC CANARD MIS- 
SILE CONFIGURATION. Walter C. Nelson and 
Anthony L. Passera. August 25, 1950. 46p. 
diagrs., photo., 3 tabs. (NACA RM L50F30) 

EFFECT OF DIHEDRAL CHANGE ON THE THEO- 
RETICAL DYNAMIC LATERAL RESPONSE CHAR- 
ACTERISTICS OF A LOW -ASPECT-RATIO 
STRAIGHT-WING SUPERSONIC AIRPLANE. 
Donovan R. Heinle. December 7, 1950. 35p. diagrs., 
2 tabs. (NACA RM A50H02) 

STATIC LONGITUDINAL STABILITY A«U 
DYNAMIC CHARACTERISTICS AT HIGH ANGLES 
OF ATTACK AND AT LOW REYNOLDS NUMBERS 
OF A MODEL OF THE X-3 SUPERSONIC RESEARCH 
AIRPLANE. Sanger M. Burk, Jr. and Burton E. 
Hultz. February 6, 1951. 76p. diagrs., photos., 
4 tabs. (NACA RM L50L19) 

THEORETICAL INVESTIGATION OF AN AUTO- 
MATIC CONTROL SYSTEM WITH PRIMARY SENSI- 
TIVITY TO NORMAL ACCELERATIONS AS USED 
TO CONTROL A SUPERSONIC CANARD MISSILE 
CONFIGURATION. Ernest C. Seaberg and Earl F. 
Smith. July 1951. 48p. diagrs., photo., 3 tabs. 
(NACA RM L51D23) 

STABILITY AND CONTROL MEASUREMENTS OB- 
TAINED DURING USAF-NACA COOPERATIVE 
FLIGHT-TEST PROGRAM ON THE X-4 AIRPLANE 
(USAF NO. 46-677). Melvin SadoH, Herman O. 
Ankenbruck and William O'Hare. October 1951. 38p. 
diagrs., photos., tab. (NACA RM A51H09) 



A THEORETICAL INVESTIGATION OF THE INFLU- 
ENCE OF AUTOPILOT NATURAL FREQUENCY 
UPON THE DYNAMIC PERFORMANCE CHARAC- 
TERISTICS OF A SUPERSONIC CANARD MISSILE 
CONFIGURATION WITH A PITCH -ATTITUDE CON- 
TROL SYSTEM. Anthony L. Passera. October 

1951. 32p. diagrs., photos., 2 tabs. (NACA 
RM L51H02) 

LONGITUDINAL FREQUENCY-RESPONSE CHAR- 
ACTERISTICS OF THE DOUGLAS D-558-I AIR- 
PLANE AS DETERMINED FROM EXPERIMENTAL 
TRANSIENT-RESPONSE HISTORIES TO A MACH 
NUMBER OF 0.90. Ellwyn E. Angle and Euclid C. 
HoUeman. February 1952. 28p. diagrs., tab. 
(NACA RM L51K28) 

A THEORETICAL INVESTIGATION OF THE 
EFFECT OF A TARGET SEEKER SENSITIVE TO 
PITCH ATTITUDE ON THE DYNAMIC STABILITY 
AND RESPONSE CHARACTERISTICS OF A SUPER- 
SONIC CANARD MISSILE CONFIGURATION. 
Ordway B. Gates, Jr. and Albert A. Schy. August 

1952. 54p. diagrs., photo., tab. (NACA 
RM L52E19) 

PRELIMINARY EXPERIMENTAL INVESTIGATION 
OF THE FLIGHT OF A PERSON SUPPORTED BY A 
JET THRUST DEVICE ATTACHfcD TO HE FEET. 
C. H. Zimmerman, Paul R. Hill and T. L. Kennedy. 
January 1953. 31p. diagrs., photos., 2 tabs. 
(NACA RM L52D10) 

THE EFFECT OF CONTROL-SURFACE-SERVO 
NATURAL FREQUENCY ON THE DYNAMIC PER- 
FORMANCE CHARACTERISTICS OF AN ACCELER- 
ATION CONTROL SYSTEM APPLIED TO A SUPER- 
SONIC MISSILE. Anthony L. Passera and Martin L. 
Nason. September 1953. 28p. diagrs., 3 tabs. 
(NACA RM L53G23a^ 

DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A CASCADE-WING VERTICALLY RISING 
AIRPLANE MODEL IN TAKE-OFFS, LANDINGS, 
AND HOVERING FLIGHT. Marion O. McKinney, 
Louis P. Tosti and Edwin E. Davenport. June 1954, 
45p. diagrs., photos., tab. (NACA TN 3198) 

AERODYNAMIC FORCES, MOMENTS, AND STA- 
BILITY DERIVATIVES FOR SLENDER BODIES OF 
GENERAL CROSS SECTION. Alvin H. Sacks. 
November 1954.(1), 74p. diagrs., 2 tabs. (NACA 
TN 3283) 

ON THE ANALYSIS OF LINEAR AND NONLINEAR 
DYNAMICAL SYSTEMS FROM TRANSIENT- 
RESPONSE DATA. Marvin Shinbrot. December 

1954. 51p. diagrs., 6 tabs. (NACA TN 3288) 

THE LINEARIZED EQUATIONS OF MOTION 
UNDERLYING THE DYNAMIC STABILITY OF AIR- 
CRAFT, SPINNING PROJECTILES, AND SYM- 
METRICAL MISSILES. A. C. Charters. January 

1955. 102p. diagrs. (NACA TN 3350) 

FLIGHT TESTING BY RADIO REMOTE CONTROL - 
FLIGHT EVALUATION OF A BEEP-CONTROL 
SYSTEM. Howard L. Turner, John S. White and 
Rudolph D. Van Dyke, Jr. March 1955. 55p. 
diagrs., photos., tab. (NACA TN 3496. Formerly 
RM A52A29) 

THEORETICAL INVESTIGATION OF A 
PROPORTIONAL-PLUS-FLICKER AUTOMATIC 
PILOT. Ernest C. Seaberg. May 1955. 53p. 
diagrs., photo., tab. (NACA TN 3427. Formerly 
RM L50I19) 

HOVERING FLIGHT TESTS OF A FOUR-ENGINE- 
TRANSPORT VERTICAL TAKE-OFF AIRPLANE 
MODEL UTILIZING A LARGE FLAP AND EXTEN- 
SIBLE VANES FOR REDIRECTING THE PROPEL- 
LER SLIPSTREAM. Louis P. Tosti and Edwin E. 
Davenport. May 1955. 26p. diagrs., photos., tab. 
(NACA TN 3440) 



AERODYNAMICS 
STABILITY AND CONTROL (1.8) 



91 



Longitudinal 
(1.8.1.2.1) 

LONGITUDINAL STABIUTY AND CONTROL CHAB- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
WITH A SWEPT -BACK TAIL FROM TESTS AT 
TRANSONIC SPEEDS BY THE NACA WING-FLOW 
METHOD. John A. Zalovcik and Richard H. Sawyer. 
March 28, 1947, 3Qp. dlagrs., photos., tab. (NACA 
RM L6K21) 

AN ANALYSIS OF LONGITUDINAL -CONTROL 
PROBLEMS ENCOUNTERED IN FLIGHT AT TRAN- 
SONIC SPEEDS WITH A JET-PROPELLED AIR- 
PLANE. Harvey H. Brown, L. Stewart Rolls and 
Lawrence A. Clousing. September 25, 1947. 56p. 
diagrs., photos., 3 tabs. (NACA RM A7G03) 

GENERAL HANDLING-QUALITIES RESULTS 
OBTAINED DURING ACCEPTANCE FUGHT TESTS 
OF THE BELL XS-1 AIRPLANE. Walter C. 
Williams, Charles M. Forsyth and Beverly P. 
Brown. April 19, 1948. 72p. diagrs., photos., tab. 
(NACA RM L8A09) 

CURRENT STATUS OF LONGITUDINAL STABILITY. 
Charles J. Donlan. May 24, 1948. 16p. diagrs. 
(NACA RM L8A28) 

SUMMARY OF RESULTS OF TUMBLING INVESTI- 
GATIONS MADE IN THE LANGLEY 20-FOOT FREE- 
SPINNING TUNNEL ON 14 DYNAMIC MODELS. 
Ralph W. Stone, Jr. and Robert L. Bryant. 
December 31, 1948. 91p. diagrs., photos., 23 tabs. 
(NACA RM L8J28) 

AN EMPIRICAL CRITERION FOR FIN STABI- 
LIZING JETTISONABLE NOSE SECTIONS OF AIR- 
PLANES. Stanley H. Scher. December 8, 1949. 
21p. diagrs., photo., tab. (NACA RM L9I28) 

SPDJ-TUNNEL INVESTIGATION OF A MODEL OF 
A 60° DELTA -WING AIRPLANE TO DETERMINE 
THE SPIN, RECOVERY, AND LONGITUDINAL 
TRIM CHARACTERISTICS THROUGHOUT AN 
EXTENSIVE RANGE OF MASS LOADINGS. Walter 
J. Klinar and Ira P. Jones, Jr. February 15, 1950. 
56p. diagrs. , photos. , 6 charts, 4 tabs. 
(NACA RM L9L06) 

LONGITUDINAL-STABILITY CHARACTERISTICS OF 
THE NORTHROP X-4 AIRPLANE (USAF NO. 46-677). 
Melvin Sadoff and Thomas R. Sisk. June 29, 1950. 
24p. diagrs., photos., tab. (NACA RM A50D27) 

PRELIMINARY EMPIRICAL DESIGN REQUIRE- 
MENTS FOR THE PREVENTION OF TUMBLING OF 
AIRPLANES HAVING NO HORIZONTAL TAILS. 
Robert L. Bryant. October 11, 1950. 23p. diagrs., 
2 tabs. (NACA RM L50H23) 

PRELIMINARY FLIGHT INVESTIGATION OF THE 
DYNAMIC LONGITUDINAL-STABILITY CHARAC- 
TERISTICS OF A 35° SWEPT-WING AIRPLANE. 
William C. Triplett and Rudolph D. Van Dyke, Jr. 
December 11, 1950. 26p. diagrs., photo., tab. 
(NACA RM A50J09a) 

SUMMARY REPORT OF RESULTS OBTAINED DUR- 
ING DEMONSTRATION TESTS OF THE NORTHROP 
X-4 AIRPLANES. Melvin Sadoff and Thomas R. 
Sisk. December 13, 1950. 46p. diagrs., photos., 
tab. (NACA RM A50I01) 

THEORETICAL INVESTIGATION OF AN AUTO- 
MATIC CONTROL SYSTEM WITH PRIMARY SENSI- 
TIVITY TO NORMAL ACCELERATIONS AS USED 
TO CONTROL A SUPERSONIC CANARD MISSILE 
CONFIGURATION. Ernest C. Seaberg and Earl F. 
Smith. July 1951. 48p. diagrs., photo., 3 tabs. 
(NACA RM L51D23) 



LONGITUDINAL FREQUENCY-RESPONSE CHARAC- 
TERISTICS OF A 35° SWEPT-WING AIRPLANE AS 
DETERMINED FROM FLIGHT MEASUREMENTS, 
INCLUDING A METHOD FOR THE EVALUATION OF 
TRANSFER FUNCTIONS. WiUiam C. Triplett and G. 
Allan Smith. September 1951. 45p. diagrs., photo. 
(NACA RM A51G27) 

LONGITUDINAL FREQUENCY-RESPONSE CHAR- 
ACTERISTICS OF THE DOUGLAS D-558-I AIR- 
PLANE AS DETERMINED FROM EXPERIMENTAL 
TRANSIENT -RESPONSE HISTORIES TO A MACH 
NUMBER OF 0.90. EUwyn E. Angle and Euclid C. 
HoUeman. February 1952. 28p. diagrs., tab. 
(NACA RM L51K28) 

FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW-SPEED STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A MODEL HAVING A FUSELAGE 
OR RELATIVELY FLAT CROSS SECTION. John W. 
Paulson and Joseph L. Johnson, Jr. February 1953. 
30p. diagrs., photo., tab. (NACA RM L52L22) 

THE EFFECT OF CONTROL-SUHFACE-SERVO 
NATURAL FREQUENCY ON THE DYNAMIC PER- 
FORMANCE CHARACTERISTICS OF AN ACCELER- 
ATION CONTROL SYSTEM APPLIED TO A SUPER- 
SONIC MISSILE. Anthony L. Passera and Martin L. 
Nason. September 1953. 28p. diagrs., 3 tabs. 
(NACA RM L53G23a) 

MATRIX METHODS FOR DETERMINING THE 
LONGITUDINAL -STABILITY DERIVATIVES OF AN 
AIRPLANE FROM TRANSIENT FLIGHT DATA. 
James J. Donegan. 1954. ii, 20p. diagrs., 6 tabs. 
(NACA Rept. 1169. Formerly TN 2902) 

AN INVESTIGATION OF THE USE OF ROCKET- 
POWERED MODELS FOR GUST-LOAD STUDIES 
WITH AN APPLICATION TO A TAILLESS SWEPT- 
WING MODEL AT TRANSONIC SPEEDS. A. James 
Vitale, H. Press and C. C. Shufflebarger. June 
1954. 36p. diagrs., photos., tab. (NACA TN 3161) 

SOME MEASUREMENTS OF ATMOSPHERIC 
TURBULENCE OBTAINED FROM FLOW-DIRECTION 
VANES MOUNTED ON AN AIRPLANE. Robert G. 
Chilton. November 1954. 22p. diagrs., photo., 
tab. (NACA TN 3313) 

A THEORETICAL INVESTIGATION OF THE 
SHORT -PERIOD DYNAMIC LONGITUDINAL 
STABILITY OF AIRPLANE CONFIGURATIONS 
HAVING ELASTIC WINGS OF 0° TO 60° SWEEP - 
BACK. Milton D. McLaughlin. December 1954. 
39p. diagrs., 2 tabs. (NACA TN 3251) 

DESCRIPTION AND ANALYSIS OF A ROCKET - 
VEHICLE EXPERIMENT ON FLUTTER INVOLVING 
WING DEFORMATION AND BODY MOTIONS. H. J. 
Cunningham and R. R. Lundstrom. January 1955. 
26p. diagrs., photos., 2 tabs. (NACA TN 3311. 
Formerly RM L50I29) 

A WIND-TUNNEL TEST TECHNIQUE FOR 
MEASURING THE DYNAMIC ROTARY STABILITY 
DERIVATIVES INCLUDING THE CROSS DERIVA- 
TIVES AT HIGH MACH NUMBERS. Benjamin H. 
Beam. January 1955. 35p. diagrs., photos. 
(NACA TN 3347) 

GROUND-SIMULATOR STUDY OF THE EFFECTS 
OF STICK FORCE AND DISPLACEMENT ON 
TRACKING PERFORMANCE. Stanley Faber. 
April 1955. 21p. diagrs., photos. (NACA TN 3428) 

THEORETICAL INVESTIGATION OF A 
PROPORTIONAL-PLUS-FLICKER AUTOMATIC 
PILOT. Ernest C. Seaberg. May 1955. 53p. 
diagrs., photo., tab. (NACA TN 3427. Formerly 
RM L50I19) 



AERODYNAMICS 
92 STABILITY AND CONTROL (1.8) 



Longitudinal Dynamic Staoility 
(Cont. ) 

TOTAL LIFT AND. PITCHING MOMENT ON THIN 
ARROWHEAD WINGS OSCILLATING IN SUPERSONIC 
POTENTIAL FLOW. H. J. Cunningham. May 1955. 
43p. diagrs., 4 tabs. (NACA TN 3433) 

Lateral and Directional 
(1.8. 1.2.2) 

GENERAL HANDLING-QUALITIES RESULTS 
OBTAINED DURING ACCEPTANCE FUGHT TESTS 
OF THE BELL XS-1 AIRPLANE. Walter C. 
Williams, Charles M. Forsyth and Beverly P. 
Brown. April 19, 1948. 72p. diagrs., photos., tab. 
(NACA RM L8A09) 

FACTORS AFFECTING LATERAL STABILITY AND 
CONTROLLABILITY. John P. CampbeU and 
Thomas A. Toll. May 13, 1948. 19p. diagrs. 
(NACA RM L8A28a) 

THEORETICAL ANALYSIS OF THE ROLLING 
MOTIONS OF AIRCRAFT USING A FLICKER-TYPE 
AUTOMATIC ROLL STABILIZATION SYSTEM 
HAVING A DISPLACEMENT-PLUS-RATE 
RESPONSE. Howard J. Curfman, Jr. January 12, 
1949. 29p. diagrs., 2 tabs. (NACA RM L8K23a) 

THEORETICAL INVESTIGATION OF THE DYNAMIC 
LATERAL STABILITY CHARACTERISTICS OF 
DOUGLAS DESIGN NO. 39C, AN EARLY VERSION 
OF THE X-3 RESEARCH AIRPLANE. Charles V. 
Bennett. January 18, 1949. 39p. diagrs., 2 tabs. 
(NACA RM L8L31) 

AN EXPERIMENTAL INVESTIGATION OF A GYRO- 
ACTUATED ROLL CONTROL SYSTEM INSTALLED 
IN A SUBSONIC TEST VEHICLE. Jerome M. 
Teltelbaum and Ernest C. Seaberg. April 20, 1949. 
26p. diagrs., photos., tab. (NACA RM L9B24a) 

MEASURIMENT OF THE DYNAMIC LATERAL 
STABILITY OF THE DOUGLAS D-558-1 AIRPLANE 
(BUAERO NO. 37971) IN RUDDER KICKS AT A MACH 
NUMBER OF 0.72. Hubert M. Drake. May 31, 1949. 
lOp. diagrs., photos. (NACA RM L9D06a) 

EFFECT OF SWEEPBACK ON THE LOW -SPEED 
STATIC AND ROLUNG STABILITY DERIVATIVES 
OF THIN TAPERED WINGS OF ASPECT RATIO 4. 
William Letlco and Walter D. Wolhart. August 9, 

1949. 36p. diagrs., photo. (NACA RM L9F14) 

AN EMPIRICAL CRITERION FOR FIN STABI- 
LIZING JETTISONABLE NOSE SECTIONS OF AIR- 
PLANES. Stanley H. Scher. December 8, 1949. 
21p. diagrs., photo., tab. (NACA RM L9I28) 

A STUDY OF THE DYNAMIC STABILITY OF THE 
BELL X-1 RESEARCH AIRPLANE. Edward C. 
Polhamus. January 10, 1950. 16p. diagrs., tab. 
(NACA RM L9K04a) 

THEORETICAL INVESTIGATION OF THE DYNAMIC 
LATERAL STABILITY CHARACTERISTICS OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE, STUDY 
41-B. Charles V. Bennett. April 27, 1950. 31p. 
diagrs., 3 tabs. (NACA RM L50B28) 

FLIGHT INVESTIGATION OF THE AILERON CHAR- 
ACTERISTICS OF THE DOUGLAS D-558-1 AIR- 
PLANE (BUAERO NO. 37972) AT MACH NUMBERS 
BETWEEN 0.6 AND 0.89. Jim Rogers Thompson, 
William S. Roden and John M. Eggleston. May 26, 

1950. 23p. diagrs., photos., tab. (NACA 
RM L50D20) 

EFFECT OF DIHEDRAL CHANGE ON THE THEO- 
RETICAL DYNAMIC LATERAL RESPONSE CHAR- 
ACTERISTICS OF A LOW-ASPECT-RATIO 
STRAIGHT -WING SUPERSONIC AIRPLANE. 
Donovan R. Heinle. December 7, 1950. 35p. diagrs., 
2 tabs. (NACA RM A50H02) 



EFFECTS ON THE LATERAL OSCILLATION OF 
FIXING THE RUDDER AND REFLEXING THE 
FLAPS ON THE BELL X-1 AIRPLANE. Hubert M. 
Drake. December 11, 1950. 14p. diagrs., photo. 
(NACA RM L50I05) 

SUMMARY REPORT OF RESULTS OBTAINED DUR- 
ING DEMONSTRATION TESTS OF THE NORTHROP 
X-4 AIRPLANES. Melvin Sadoff and Thomas R. 
Sisk. December 13, 1950. 46p. diagrs., photos., 
tab. (NACA RM A50I01) 

EFFECTS ON THE SNAKING OSCILLATION OF THE 
BELL X-1 AIRPLANE OF A TRAILING-EDGE BULB 
ON THE RUDDER. Hubert M. Drake and Harry P. 
Clagett. January 16, 1951. 14p. diagrs., photo. 
(NACA RM L50K01a) 

THE EFFECT OF MASS DISTRIBUTION ON THE 
LOW-SPEED DYNAMIC LATERAL STABILITY AND 
CONTROL CHARACTERISTICS OF A MODEL WITH 
A 60° TRIANGULAR WING. Joseph L. Johnson. 
March 9, 1951. 23p. diagrs., 2 tabs. (NACA 
RM L50K10) 

A COMPARISON OF THE MEASURED AND PRE- 
DICTED LATERAL OSCILLATORY CHARACTER- 
ISTICS OF A 35° SWEPT-WING FIGHTER AIR- 
PLANE. Walter E. McNeill and George E. Cooper. 
July 1951. 21p. diagrs., 3 tabs. (NACARM A51C28) 

A FLIGHT STUDY OF REQUIREMENTS FOR SATIS- 
FACTORY LATERAL OSCILLATORY CHARACTER- 
ISTICS OF FIGHTER AIRCRAFT. Charles J. 
Liddell, Jr., Brent Y. Creer and Rudolph D. 
Van Dyke, Jr. July 1951. 39p. diagrs., photo., 
2 tabs. (NACA RM A51E16) 

SYSTEM ANALYSES AND AUTOPILOT DESIGN FOR 
AUTOMATIC ROLL STABILIZATION OF A SUPER- 
SONIC PILOTLESS AIRCRAFT. Jacob Zarovsky. 
July 1951. 55p. diagrs., tab. (NACA RM L51E07) 

LOW-SPEED TESTS OF A FREE-TO-YAW MODEL 
IN TWO WIND TUNNELS OF DIFFERENT TURBU- 
LENCE. Jones F. Cahill and John D. Bird. 
February 1952. 12p. diagrs., photos. (NACA 
RM L51L14) 

FLIGHT MEASUREMENTS OF THE LATERAL STA- 
BILITY AND CONTROL CHARACTERISTICS OF A 
HIGH-SPEED FIGHTER AIRPLANE. H. L. Crane, 
A. R. Beckhardt and C. E. Matheny. September 
1952. 50p. diagrs., tab. (NACA RM L52B14) 

LATERAL AND DIRECTIONAL DYNAMIC - 
RESPONSE CHARACTERISTICS OF A 35° SWEPT- 
WING AIRPLANE AS DETERMINED FROM FLIGHT 
MEASUREMENTS. William C. Triplett and 
Stuart C. Brown. December 1952. 62p. diagrs., 
photo,, 3 tabs. (NACA RM A52I17) 

THE EFFECTS ON DYNAMIC LATERAL STABILITY 
AND CONTROL OF LARGE ARTIFICIAL VARIA- 
TIONS IN THE ROTARY STABIUTY DERIVATIVES. 
Robert O. Schade and James L. Hassell, Jr. 1953. 
U, 24p. diagrs., photo., 2 tabs. (NACA Rept. 1151. 
Formerly TN 2781) 

FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW -SPEED STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A MODEL HAVING A FUSELAGE 
OR RELATIVELY FLAT CROSS SECTION. John W. 
Paulson and Joseph L. Johnson, Jr. February 1953. 
30p. diagrs., photo., tab. (NACA RM L52L22) 

THEORETICAL CALCULATIONS OF THE LATERAL 
STABILITY DERIVATIVES FOR TRIANGULAR VER- 
TICAL TAILS WITH SUBSONIC LEADING EDGES 
TRAVELING AT SUPERSONIC SPEEDS. Percy J. 
Bobbitt. December 1954. 68p. diagrs., photos., 
5 tabs. (NACA TN 3240) 



AERODYNAMICS 
STABILITY AND CONTROL (1.8) 



93 



Lateral and Directional Dynamic 
Stability (Cont. ) 

A SYSTEM FOR MEASURING THE DYNAMIC LAT- 
ERAL STABILITY DERIVATIVES IN HIGH-SPEED 
WIND TUNNELS. Henry C. Leasing, Thomas B. 
Fryer and Merrill H. Mead. December 1954. 42p. 
diagrs., photo. (NACA TN 3348) 

A WIND-TUNNEL TEST TECHNIQUE FOR 
MEASURING THE DYNAMIC ROTARY STABILITY 
DERIVATIVES INCLUDING THE CROSS DERIVA- 
TIVES AT HIGH MACH NUMBERS. Benjamin H. 
Beam. January 1955. 35p. diagrs., photos. 
(NACA TN 3347) 

EFFECT OF LAG OF SIDEWASH ON THE 
VERTICAL-TAIL CONTRIBUTION TO OSCIL- 
LATORY DAMPING IN YAW OF AIRPLANE 
MODELS. Lewis R. Fisher and Herman S. 
Fletcher. January 1955. 38p. diagrs., photos. 
(NACA TN 3356) 

THEORETICAL CALCULATIONS OF THE PRES- 
SURES, FORCES, AND MOMENTS DUE TO 
VARIOUS LATERAL MOTIONS ACTING ON THIN 
ISOLATED VERTICAL TAILS WITH SUPERSONIC 
LEADING AND TRAILING EDGES. Kenneth 
Margolis. March 1955. 43p. diagrs., 10 tabs. 
(NACA TN 3373) 

SOME CALCULATIONS OF THE LATERAL RE- 
SPONSE OF TWO AIRPLANES TO ATMOSPHERIC 
TURBULENCE WITH RELATION TO THE LATERAL 
SNAKING PROBLEM. John D. Bird. May 1955. 
24p. diagrs., 2 tabs. (NACA TN 3425. Formerly 
RM L50F26a) 

Damping Derivatives 
(1.8.1.2.3) 

FACTORS AFFECTING LATERAL STABILITY AND 
CONTROLLABILITY. John P. CampbeU and 
Thomas A. Toll. May 13, 1948. 19p. diagrs. 
(NACA RM L8A28a) 

THEORETICAL ANALYSIS OF THE ROLLING 
MOTIONS OF AIRCRAFT USING A FLICKER-TYPE 
AUTOMATIC ROLL STABILIZATION SYSTEM 
HAVING A DISPLACEMENT-PLUS -RATE 
RESPONSE. Howard J. Curiman, Jr. January 12, 
1949. 29p. diagrs., 2 tabs. (NACA RM L8K23a) 

THEORETICAL INVESTIGATION OF THE DYNAMIC 
LATERAL STABILITY CHARACTERISTICS OF 
DOUGLAS DESIGN NO. 39C, AN EARLY VERSION 
OF THE X-3 RESEARCH AIRPLANE. Charles V. 
Bennett. January 18, 1949. 39p. diagrs., 2 tabs. 
(NACA RM L8L31) 

HHHI^SUBSONIC DAMPING-m-ROLL CHARACTEB- 
ISTICS OF A WING WITH THE QUARTER-CHORD 
LINE SWEPT BACK 35° AND WITH ASPECT RATIO 
3 AND TAPER RATIO 0.6. Boyd C. Myers, n and 
Richard E. Kuhn. May 10, 1949. Zip. diagrs., 
photo., tab. (NACA RM L9C23) 

EFFECTS OF MACH NUMBER AND SWEEP ON THE 
DAMPING-IN-ROLL CHARACTERISTICS OF WINGS 
OF ASPECT RATIO 4. Richard E. Kuhn and Boyd 
C. Myers, n. June 27, 1949. 28p. diagrs., photo. 
(NACA RM L9E10) 

DAMPING-IN-ROLL CHARACTERISTICS OF A 
42. 7° SWEPT -BACK WING AS DETERMINED FROM 
A WIND-TUNNEL INVESTIGATION OF A TWISTED 
SEMISPAN WING. Vernard E. Lockwood. August 8, 
1949. 23p. diagrs. (NACA RM L9F15) 

EFFECT OF SWEEPBACK ON THE LOW -SPEED 
STATIC AND ROLUNG STABILITY DERIVATIVES 
OF THIN TAPERED WDJGS OF ASPECT RATIO 4. 
William Letko and Walter D. Wolhart. August 9, 
1949. 36p. diagrs., photo. (NACA RM L9F14) 



WIND-TUNNEL INVESTIGATION AT LOW TRAN- 
SONIC SPEEDS OF THE EFFECTS OF NUMBER OF 
WINGS ON THE LATERAL-CONTROL EFFECTIVE- 
NESS OF AN RM-5 TEST VEHICLE. Harold S. 
Johnson. November 29, 1949. 15p. diagrs., photo., 
tab. (NACA RM L9H16) 

A FREE-FLIGHT TECHNIQUE FOR MEASURING 
DAMPING IN ROLL BY USE OF ROCKET-POWERED 
MODELS AND SOME INITIAL RESULTS FOR 
RECTANGULAR WINGS. James L. Edmondson and 
E. Claude Sanders, Jr. December 20, 1949. 25p. 
diagrs., photos. (NACA RM L9I01) 

THE EFFECT OF TIP TANKS ON THE ROLLING 
CHARACTERISTICS AT HIGH SUBSONIC MACH 
NUMBERS OF A WING HAVING AN ASPECT RATIO 
OF 3 WITH QUARTER-CHORD LINE SWEPT BACK 
35°. Richard E. Kuhn and Boyd C. Myers, U. 
January 17, 1950. 2"^. diagrs., photo., 2 tabs. 
(NACA RM L9J19) 

THE DAMPING IN ROLL OF ROCKET-POWERED 
TEST VEHICLES HAVING RECTANGULAR WINGS 
WITH NACA 65-006 AND SYMMETRICAL DOUBLE- 
WEDGE AIRFOIL SECTIONS OF ASPECT RATIO 4.5. 
Albert E. Dietz and James L. Edmondson. March 29, 
1950. 12p. diagrs. (NACA RM L50B10) 

THEORETICAL INVESTIGATION OF THE DYNAMIC 
LATERAL STABILITY CHARACTERISTICS OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE, STUDY 
41 -B. Charles V. Bennett. April 27, 1950. 31p. 
diagrs., 3 tabs. (NACA RM L50B28) 

AERODYNAMIC AND LATERAL-CONTROL CHAR- 
ACTERETICS OF A 1/28-SCALE MODEL OF THE 
BELL X-1 AIRPLANE WING-FUSELAGE COMBINA- 
TION. TRANSONIC -BUMP METHOD. Vernard E. 
Lockwood. May 5, 1950. 28p. diagrs., tab. (NACA 
RM L50C22) 

DAMPING IN ROLL OF RECTANGULAR WINGS OF 
SEVERAL ASPECT RATIOS AND NACA 65A -SERIES 
AIRFOIL SECTIONS OF SEVERAL THICKNESS 
RATIOS AT TRANSONIC AND SUPERSONIC SPEEDS 
AS DETERMINED WITH ROCKET-POWERED 
MODELS. James L. Edmondson. August 24, 1950. 
16p. diagrs. (NACA RM L50E26) 

DAMPING IN YAW AND STATIC DIRECTIONAL 
STABILITY OF A CANARD AIRPLANE MODEL AND 
OF SEVERAL MODELS HAVING FUSELAGES OF 
RELATIVELY FLAT CROSS SECTION. Joseph L. 
Johnson. October 16, 1950. 20p. diagrs., tab. 
(NACA RM L50H30a) 

EFFECT OF DIHEDRAL CHANGE ON THE THEO- 
RETICAL DYNAMIC LATERAL RESPONSE CHAR- 
ACTERISTICS OF A LOW-ASPECT-RATIO 
STRAIGHT -WING SUPERSONIC AIRPLANE. 
Donovan R. Heinle. December 7, 1950. 35p. diagrs., 
2 tabs. (NACA RM A50H02) 

PRELIMINARY FUGHT INVESTIGATION OF THE 
DYNAMIC LONGITUDINAL-STABIUTY CHARAC- 
TERISTICS OF A 35° SWEPT-WING AIRPLANE. 
William C. Triplett and Rudolph D. Van Dyke, Jr. 
December 11, 1950. 26p. diagrs., photo., tab. 
(NACA RM A50J09a) 

EFFECTS OF SWEEP ON THE DAMPING-IN-ROLL 
CHARACTERISTICS OF THREE SWEPTBACK 
WINGS HAVING AN ASPECT RATIO OF 4 AT 
TRANSONIC SPEEDS. Vernard E. Lockwood. 
December 14, 1950. 23p. diagrs. (NACA 
RM L50J19) 

THE EFFECT OF MASS DISTRIBUTION ON THE 
LOW-SPEED DYNAMIC LATERAL STABILITY AND 
CONTROL CHARACTERISTICS OF A MODEL WITH 
A 60° TRIANGULAR WING. Joseph L. Johnson. 
March 9, 1951. 23p. diagrs., 2 tabs. (NACA 
RM L50K10) 



94 



AERODYNAMICS 

STABILITY AND CONTROL (1.8) 



Damping Derivatives - Stability 
(Cont. ) 

A COMPARISON OF TWO TECHNIQUES UTILIZING 
ROCKET-PROPELLED VEHICLES FOR THE DE- 
TERMINATION OF THE DAMPING-m-ROLL 
DERIVATIVE. David G. Stone and Carl A. Sandahl. 
May 3, 1951. 17p. diagrs., photos. (NACA 
RM L51A16) 

LONGITUDINAL FREQUENCY-RESPONSE CHARAC- 
TERISTICS OF A 35° SWEPT -WING AIRPLANE AS 
DETERMINED FROM FLIGHT MEASUREMENTS, 
INCLUDING A METHOD FOR THE EVALUATION OF 
TRANSFER FUNCTIONS. WiUiam C. Triplett and G. 
Allan Smith. September 1951. 45p. diagrs., photo. 
(NACA RM A51G27) 

LONGITUDINAL FREQUENCY-RESPONSE CHAR- 
ACTERISTICS OF THE DOUGLAS D-558-I AIR- 
PLANE AS DETERMINED FROM EXPERIMENTAL 
TRANSIENT -RESPONSE HBTORIES TO A MACH 
NUMBER OF 0.90. EUwyn E. Angle and Euclid C. 
HoUeman. February 1952. 28p. diagrs., tab. 
(NACA RM L51K28) 

THE CALCULATION OF CERTAIN STATIC AERO- 
ELASTIC PHENOMENA OF WINGS WITH TIP 
TANKS OR BOOM-MOUNTED LIFTING SURFACES. 
Franklin W. Diederich and Kenneth A. Foss. 
August 1952. 55p. diagrs., 2 tabs. (NACA 
RM L52A22) 

A STUDY OF THE FLOW FIELD BEHIND THE TRI- 
ANGULAR HORIZONTAL TAIL OF A CANARD AIR- 
PLANE AT APPROXIMATELY THE VERTICAL- 
TAIL LOCATION BY MEANS OF A TUFT GRID. 
Joseph L. Johnson, Jr. October 1952. IBp. diagrs., 
tab. (NACA RM L52H11) 

LATERAL AND DIRECTIONAL DYNAMIC- 
RESPONSE CHARACTERISTICS OF A 35° SWEPT- 
WING AIRPLANE AS DETERMINED FROM FLIGHT 
MEASUREMENTS. William C. Triplett and 
Stuart C. Brown. December 1952. 62p. diagrs., 
photo., 3 tabs. (NACA RM A52I17) 

A VECTOR STUDY OF LINEARIZED SUPERSONIC 
FLOW APPLICATIONS TO NONPLANAR 
PROBLEMS. John C. Martin. 1953. ii, 34p. 
diagrs., tab. (NACA Rept. 1143. Formerly 
TN 2641) 

THE EFFECTS ON DYNAMIC LATERAL STABILITY 
AND CONTROL OF LARGE ARTIFICIAL VARIA- 
TIONS IN THE ROTARY STABIUTY DERIVATIVES. 
Robert O. Schade and Tames L. Hassell, Jr. 1953. 
il, 24p. diagrs., photo., 2 tabs. (NACA Rept. 1151. 
Formerly TN 2781) 

FREE-FLIGHT-TUNNEL INVESTIGATION OF THE 
LOW -SPEED STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A MODEL HAVING A FUSELAGE 
OR RELATIVELY FLAT CROSS SECTION. John W. 
Paulson and Joseph L. Johnson, Jr. February 1953. 
30p. diagrs., photo., tab. (NACA RM L52L22) 

METHOD FOR CALCULATING THE ROLLING AND 
YAWING MOMENTS DUE TO ROLLING FOR UN- 
SWEPT WINGS WITH OR WITHOUT FLAPS OR 
AILERONS BY USE OF NONLINEAR SECTION LIFT 
DATA. Albert P. Martina. 1954. ii, 16p. diagrs., 
11 tabs. (NACA Rept. 1167. Formerly TN 2937) 

LIFT AND PITCHING MOMENT AT SUPERSONIC 
SPEEDS DUE TO CONSTANT VERTICAL ACCELER- 
ATION FOR THIN SWEPTBACK TAPERED WINGS 
WITH STREAMWISE TIPS. SUPERSONIC LEADING 
AND TRAILING EDGES. Isabella J. Cole and 
Kenneth Margolis. July 1954. 67p. diagrs., 4 tabs. 
(NACA TN 3196) 



CALCULATED SUBSONIC SPAN LOADS AND 
RESULTING STABILITY DERIVATIVES OF UN- 
SWEPT AND 45° SWEPTBACK TAIL SURFACES IN 
SIDESLIP AND IN STEADY ROLL. M. J. Queljo 
and Donald R. Riley. October 1954. llOp. 
diagrs., 2 tabs. (NACA TN 3245) 

AERODYNAMIC FORCES, MOMENTS, AND STA- 
BILITY DERIVATIVES FOR SLENDER BODIES OF 
GENERAL CROSS SECTION. Alvin H. Sacks. 
November 1954.(i), 74p. diagrs., 2 tabs. (NACA 
TN 3283) 

THEORETICAL CALCULATIONS OF THE LATERAL 
STABILITY DERIVATIVES FOR TRIANGULAR VER- 
TICAL TAILS WITH SUBSONIC LEADING EDGES 
TRAVELING AT SUPERSONIC SPEEDS. Percy J. 
Bobbitt. December 1954. 68p. diagrs., photos., 
5 tabs. (NACA TN 3240) 

A SYSTEM FOR MEASURING THE DYNAMIC LAT- 
ERAL STABILITY DERIVATIVES IN HIGH-SPEED 
WIND TUNNELS. Henry C. Lessing, Thomas B. 
Fryer and Merrill H. Mead. December 1954. 42p. 
diagrs., photo. (NACA TN 3348) 

A WIND-TUNNEL TEST TECHNIQUE FOR 
MEASURING THE DYNAMIC ROTARY STABILITY 
DERIVATIVES INCLUDING THE CROSS DERIVA- 
TIVES AT HIGH MACH NUMBERS. Benjamin H. 
Beam. January 1955. 35p. diagrs., photos. 
(NACA TN 3347) 

EFFECT OF LAG OF SIDEWASH ON THE 
VERTICAL-TAIL CONTRIBUTION TO OSCIL- 
LATORY DAMPING IN YAW OF AIRPLANE 
MODELS. Lewis R. Fisher and Herman S. 
Fletcher. January 1955. 38p. diagrs., photos. 
(NACA TN 3356) 

THEORETICAL CALCULATIONS OF THE PRES- 
SURES, FORCES, AND MOMENTS DUE TO 
VARIOUS LATERAL MOTIONS ACTING ON THIN 
ISOLATED VERTICAL TAILS WITH SUPERSONIC 
LEADING AND TRAILING EDGES. Kenneth 
Margolis. March 1955. 43p. diagrs., 10 tabs. 
(NACA TN 3373) 

A TECHNIQUE UTILIZING ROCKET-PROPELLED 
TEST VEHICLES FOR THE MEASUREMENT OF 
THE DAMPING IN ROLL OF STING-MOUNTED 
MODELS AND SOME INITIAL RESULTS FOR DELTA 
AND UNSWEPT TAPERED WINGS. WiUiam M. 
Bland, Jr. and Carl A. Sandahl. May 1955. 25p. 
diagrs., photos., tab. (NACA TN 3314. Formerly 
RM L50D24) 

TOTAL LIFT AND PITCHING MOMENT ON THIN 
ARROWHEAD WINGS OSCILLATING IN SUPERSONIC 
POTENTIAL FLOW. H. J. Cunningham. May 1955. 
43p. diagrs., 4 tabs. (NACA TN 3433) 

CONTROL 
(1.8.2) 

WIND-TUNNEL INVESTIGATION AT MACH NUM- 
BERS FROM 0.50 TO 1.20 OF AN ALL-MOVABLE 
TRIANGULAR WING OF ASPECT RATIO 4 ALONE 
AND WITH A BODY. Louis S. Stivers, Jr. and 
Alexander W. Malick. February 2, 1950. 45p. 
diagrs., photos., tab. (NACA RM A9L01) 

THE TIME LAG BETWEEN FLAP DEFLECTION 
AND FORCE DEVELOPMENT AT A MACH NUMBER 
OF 4. Walter F. Lindsey and Edward F. Ulmann. 
February 13, 1950. lip. diagr., photos. (NACA 
RM L9L15) 



AERODYNAMICS 
STABILITY AND CONTROL (1.8) 



95 



Control (Cont. ) 



WIND-TUNNEL INVESTIGATION AT MACH 
NUMBERS FROM 0.50 TO 1.29 OF AN UNSWEPT 
TAPERED WING OF ASPECT RATIO 2.67 WITH 
LEADING- AND TRAILDJG-EDGE FLAPS - 
TRAILING-EDGE FLAPS DEFLECTED. Louis S. 
Stivers, Jr. and Alexander W. Malick. 
December 13, 1950. 45p. diagrs., photo., 5 tabs. 
(NACA RM A50J09b) 

WIND-TUNNEL INVESTIGATION AT MACH NUM- 
BERS FHOM 0.50 TO 1.29 OF AN UNSWEPT, 
TAPERED WING OF ASPECT RATIO 2.67 WITH 
LEADING- AND TRAIUNG-EDGE FLAPS - 
LEADING-EDGE FLAPS DEFLECTED. Louis S. 
Stivers, Jr. and Alexander W. Malick. February 26, 
1951. 37p. diagrs., photo., 5 tabs. (NACA 
RM A50K10) 

PRELIMINARY EXPERIMENTAL INVESTIGATION 
OF THE FLIGHT OF A PERSON SUPPORTED BY A 
JET THRUST DEVICE ATTACHED TO HIS FEET. 
C. H. Zimmerman, Paul R. Hill and T. L. Kennedy. 
January 1953. 31p. diagrs., photos., 2 tabs. 
(NACA RM L52D10) 

LONGITUDINAL CONTROL 
(1.8.2. 1) 

LONGITUDINAL STABIUTY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN AIRPLANE MODEL 
WITH A SWEPT -BACK TAIL FROM TESTS AT 
TRANSONIC SPEEDS BY THE NACA WING-FLOW 
METHOD. John A. Zalovcik and Richard H. Sawyer. 
March 28, 1947. 30p. diagrs., photos., tab. (NACA 
RM L6K21) 

FORCE AND LONGITUDINAL CONTROL CHARAC- 
TERISTICS OF A 1/16 - SCALE MODEL OF THE 
BELL XS-1 TRANSONIC RESEARCH-AIRPLANE AT 
HIGH MACH NUMBERS. Axel T. Mattson. May 21, 

1947. 32p. diagrs., photo., tab. (NACA RM L7A03) 

AN ANALYSIS OF LONGITUDINAL -CONTROL 
PROBLEMS ENCOUNTERED IN FLIGHT AT TRAN- 
SONIC SPEEDS WITH A JET-PROPELLED AIR- 
PLANE. Harvey H. Brown, L. Stewart Rolls and 
Lawrence A. Clousing. September 25, 1947. 56p. 
diagrs., photos., 3 tabs. (NACA RM A7G03) 

HIGH-SPEED WIND-TUNNEL TESTS OF A MODEL 
PURSUIT AIRPLANE AND CORRELATION WITH 
FLIGHT -TEST RESULTS. Joseph W. Cleary and 
Lyle J. Gray. January 21, 1948. 56p. diagrs., 
photos. (NACA RM A7I16) 

WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 1.53 OF AN AIRPLANE WITH A TRIANGU- 
LAR WING. Richard Scherrer and William R. 
Wimbrow. January 23, 1948. 74p. diagrs., 
photos., 2 tabs. (NACA RM A7J05) 

GENERAL HANDLING-QUALITIES RESULTS 
OBTAINED DURING ACCEPTANCE FLIGHT TESTS 
OF THE BELL XS-1 AIRPLANE. Walter C. 
Williams, Charles M. Forsyth and Beverly P. 
Brown. April 19, 1948. 72p. diagrs., photos., tab. 
(NACA RM L8A09) 

HIGH-SPEED WIND-TUNNEL TESTS OF A 1/78- 
SCALE MODEL OF THE LOCKHEED YP-80A AIR- 
PLANE. Robert N. Olson and Leslie F. Lawrence. 
May 28, 1948. 52p. diagrs., photos. (NACA RM 
A7L24) 

FORCE, STATIC LONGITUDINAL STABILITY, AND 
CONTROL CHARACTERISTICS OF A 1/16-SCALE 
MODEL OF THE BELL XS-1 TRANSONIC RE- 
SEARCH AIRPLANE AT HIGH MACH NUMBERS. 
Axel T. Mattson and Donald L. Loving. June 23, 

1948. 49p. diagrs., tab. (NACA RM L8A12) 



HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE. LONGITUDINAL STABILITY AND CON- 
TROL OF THE D-558-1. John B. Wright. July 8, 

1948. 47p. diagrs., tab. (NACA RM L8C23) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERBTICS OF A SEMISPAN AIRPLANE MODEL 
AT TRANSONIC SPEEDS AS OBTAINED BY THE . 
TRANSONIC -BUMP METHOD. Joseph Weil and 
M. Leroy Spearman. July 19, 1948. 23p. diagrs., 
tab. (NACA RM L8B03) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERSTICS OF A SEMISPAN AIRPLANE MODEL 
WITH A SWEPTBACK WING AND TAIL FROM 
TESTS AT TRANSONIC SPEEDS BY THE NACA 
WING-FLOW METHOD. Richard H. Sawyer and 
Lindsay J. Lina. July 23, 1948. 42p. diagrs., 
photos., tab. (NACA RM L8B19) 

LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A SEMISPAN MODEL OF A 
SUPERSONIC AIRPLANE CONFIGURATION AT 
TRANSONIC SPEEDS FROM TESTS BY THE NACA 
WING- FLOW METHOD. Norman S. Silsby and 
James M. McKay. November 8, 1948. 30p. 
diagrs., photos., tab. (NACA RM L8G30) 

DETERMINATION BY THE FREE-FALL METHOD 
OF THE LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A 1/4-SCALE MODEL OF 
THE BELL XS-1 AIRPLANE AT TRANSONIC 
SPEEDS. James T. Matthews, Jr. and Charles W. 
Mathews. November 9, 1948. 19p. diagrs., 
photo., tab. (NACA RM L8G29a) 

SUMMARY OF RESULTS OF TUMBLING INVESTI- 
GATIONS MADE IN THE LANGLEY 20-FOOT FREE- 
SPINNING TUNNEL ON 14 DYNAMIC MODELS. 
Ralph W. Stone, Jr. and Robert L. Bryant. 
December 31, 1948. 91p. diagrs., photos., 23 tabs. 
(NACA RM L8J28) 

STABILITY RESULTS OBTAINED WITH DOUGLAS 
D-558-1 AIRPLANE (BUAERO NO. 37971) IN 
FLIGHT UP TO A MACH NUMBER OF 0.89. 
William H. Barlow and Howard C. Lilly. April 22, 

1949. 16p. diagrs., photos. (NACA RM L8K03) 

THE AERODYNAMIC CHARACTERISTICS THROUGH- 
OUT THE SUBSONIC SPEED RANGE OF A THIN, 
SHARP-EDGED HORIZONTAL TAIL OF ASPECT 
RATIO 4 EQUIPPED WITH A CONSTANT -CHORD 
ELEVATOR. Angelo Bandettini and Verlin D. Reed. 
June 30, 1949. 50p. diagrs., photo. (NACA 
RM A9E05) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH UNSWEPT 
QUARTER -CHORD LINE, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. 
Alexander D. Hammond. March 10, 1950. 20p. 
diagrs. (NACA RM L50A03) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LONGITUDINAL STABILITY AND CON- 
TROL. William B. Kemp, Jr. Robert E. Becht and 
Albert G. Few, Jr. March 14, 1950. 51p. diagrs., 
photos. (NACA RM L9K08) 

INVESTIGATION AT HIGH SUBSONIC SPEEDS OF A 
45° SWEPTBACK HORIZONTAL TAIL WITH PLAIN 
AND HORN-BALANCED CONTROL SURFACES. 
Harold S. Johnson and Robert F. Thompson. 
March 31, 1950. 44p. diagrs., photo., tab. (NACA 
RM L50B13) 

LOW -SPEED INVESTIGATION OF DEFLECTABLE 
WING-TIP ELEVATORS ON A LOW -ASPECT -RATIO 
UNTAPERED 45° SWEPTBACK SEMISPAN WING 
WITH AND WITHOUT AN END PLATE. Jack 
Fischel and William M. O'Hare. June 1, 1950. 21p. 
diagrs., photo. (NACA RM L50D19) 



AERODYNAMICS 
96 STABILITY AND CONTROL, (1.8) 



Longitudinal Control (Cont. ) 

WING-FLOW MEASUREMENTS OF LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
A CANARD AIRPLANE CONFIGURATION WITH A 
45° SWEPTBACK WING AND A TRIANGULAR ALL- 
MOVABLE CONTROL SURFACE. Harold L. Crane 
and James J. Adams. August 25, 1950. 53p. 
diagrs., photo. (NACA RM L50A3 1) 

LOW -SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL oiF THE X-3 AIRPLANE - LONGITUDINAL 
CHARACTERISTICS. Noel K. Delany and Nora-Lee 
F. Hayter. September 8, 1950. 80p. diagrs.. 
photos., 2 tabs. (NACA RM A50G06) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AT HIGH-SUBSONIC SPEEDS OF TWO 
MODELS OF A TRANSONIC RESEARCH AIRPLANE 
WITH WINGS AND HORIZONTAL TAILS OF ASPECT 
RATIOS 4.2 AND 2. Arvo A. Luoma and John B. 
Wright. September 29, 1950. 134p. diagrs., photos., 
3 tabs. (NACA RM L50H07) 

LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBER OF 1.24 OF 1/30-SCALE SEMISPAN 
MODEL OF BELL X-5 VARIABLE-SWEEP AIR- 
PLANE WITH WING SWEPT BACK 60° FROM TESTS 
BY NACA WING-FLOW METHOD. Norman S. 
Silsby, Garland J. Morris and Robert M. Kennedy. 
October 12, 1950. 17p. diagrs., photos., tab. 
(NACA RM L50E02a) 

PRELIMINARY FLIGHT INVESTIGATION OF THE 
DYNAMIC LONGITUDINAL-STABILITY CHARAC- 
TERISTICS OF A 35° SWEPT -WING AIRPLANE. 
William C. Trlplett and Rudolph D. Van Dyke, Jr. 
December 11, 1950. 26p. diagrs., photo., tab. 
(NACA RM A50J09a) 

STABILITY AND CONTROL CHARACTERISTICS OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL IN 
THE LANDING CONFIGURATION. Robert E. Becht. 
December 18, 1950. 38p. diagrs., photos. (NACA 
RM L50J27) 

LONGITUDINAL-CONTROL EFFECTIVENESS AND 
DOWNWASH CHARACTERISTICS AT A MACH NUM- 
BER OF 1.24 OF A 1/30-SCALE SEMISPAN MODEL 
OF THE BELL X-5 AIRPLANE AS DETERMINED BY 
THE NACA Wing-flow method. Richard H. 
Sawyer, Robert M. Kennedy and Garland J. Morris. 
January 8, 1951. 37p. diagrs., photos., tab. 
(NACA RM L50K15) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 60° DELTA WING EQUIPPED WITH A 
TRIANGULAR PLAN-FORM CONTROL HAVING A 
SKEWED HINGE AXIS AND AN OVERHANG BAL- 
ANCE. TRANSONIC-BUMP METHOD. Harleth G. 
Wiley. February 6, 1951. 31p. diagrs. (NACA 
RML50L01) 

AERODYNAMIC CHARACTERISTICS AT TRAN- 
SONIC SPEEDS OF A TAPERED 45° SWEPTBACK 
WING OF ASPECT RATIO 3 HAVING A FULL-SPAN 
FLAP-TYPE CONTROL. TRANSONIC-BUMP 
METHOD. Vernard E. Lockwood and Joseph E. 
Fikes. August 1951. 35p. diagrs. (NACA 
RM L51F06a) 

LONGITUDINAL FREQUENCY-RESPONSE CHARAC- 
TERISTICS OF A 35° SWEPT -WING AIRPLANE AS 
DETERMINED FROM FUGHT MEASUREMENTS, 
INCLUDING A METHOD FOR THE EVALUATION OF 
TRANSFER FUNCTIONS. WiUiam C. Triplett and G. 
Allan Smith. September 1951. 45p. diagrs., photo. 
(NACA RM A51G27) 



A METHOD FOR THE DESIGN OF SWEPTBACK 
WINGS WARPED TO PRODUCE SPECIFIED FUGHT 
CHARACTERISTICS AT SUPERSONIC SPEEDS. 
Warren A. Tucker. September 1951. 52p. diagrs., 
2 tabs. (NACA RM L51F08) 

AN INVESTIGATION AT TRANSONIC SPEEDS OF 
THE EFFECTS OF CONTROL CHORD AND SPAN 
ON THE CONTROL CHARACTERISTICS OF A 
TAPERED WEDGE -TYPE WING OF ASPECT RATIO 
2.5. TRANSONIC -BUMP METHOD. Raymond D. 
Vogler, Vernard E. Lockwood and Thomas R. 
Turner. September 1951. 36p. diagrs. (NACA 
RM L51G03) 

MEASUREMENTS IN FLIGHT OF THE LONGITUDI- 
NAL CHARACTERISTICS OF TWO JET AIRCRAFT, 
ONE WITH A DIVING TENDENCY AND THE OTHER 
WITH A CLIMBING TENDENCY AT HIGH MACH 
NUMBERS. Seth B. Anderson. October 1951. 18p. 
diagrs., photos., 2 tabs. (NACA RM A51E14) 

A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT -WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
Seth B. Anderson and Richard S. Bray. November 
1951. 33p. diagrs., photo., tab. (NACA RM A51I12) 

INVESTIGATION OF WING-TIP AILERONS ON A 
51.3° SWEPTBACK WING AT TRANSONIC SPEEDS 
BY THE TRANSONIC-BUMP METHOD. William C. 
Moseley, Jr. and James M. Watson. November 1951. 
60p. diagrs. (NACARM L51H27) 

EFFECTS OF HORIZONTAL-TAIL POSITION, AREA, 
AND ASPECT RATIO ON LOW-SPEED STATIC 
LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A 60° TRIANGULAR-WING 
MODEL HAVING VARIOUS TRIANGULAR- ALL- 
MOVABLE HORIZONTAL TAILS. Byron M. Jaquet. 
December 1951. 61p. diagrs., photo., tab. (NACA 
RM L51I06) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A TAPERED 45° SWEPTBACK WING 
OF ASPECT RATIO 3 HAVING A FULL-SPAN FLAP 
TYPE OF CONTROL WITH OVERHANG BALANCE. 
TRANSONIC -BUMP METHOD. Vernard E. 
Lockwood and John R. Hagerman. January 1952. 
24p. diagrs. (NACA RM L51L11) 

LOW -SPEED STATIC LONGITUDINAL STABILITY 
AND CONTROL CHARACTERISTICS OF 60° 
TRIANGULAR-WING AND MODIFIED 60° 
TRIANGULAR-WING MODELS HAVING HALF- 
DELTA AND HALF-DIAMOND TIP CONTROLS. 
Jacob H. Lichtenstein and Byron M. Jaquet. 
February 1952. 36p. diagrs., photos., tab. (NACA 
RM L51K08) 

HINGE -MOMENT AND OTHER AERODYNAMIC 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
QUARTER-SPAN SPOILER ON A TAPERED 45° 
SWEPTBACK WING OF ASPECT RATIO 3. 
Joseph E. Fikes. February 1952. 22p. diagrs., 
photo. (NACA RM L52A03) 

EFFECTS OF HORIZONTAL-TAIL POSITION AND 
ASPECT RATIO ON LOW-SPEED STATIC LONGI- 
TUDINAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF A 60° TRIANGULAR -WING MODEL HAV- 
ING TWIN TRIANGULAR ALL-MOVABLE TAILS. 
Byron M. Jaquet. May 1952. 45p. diagrs., photos. 
(NACA RM L52B25) 

AN INVESTIGATION OF LONGITUDINAL CONTROL 
CHARACTERISTICS OF A WING-TIP CONTROL 
SURFACE ON A SWEPTBACK WING AT TRANSONIC 
SPEEDS BY THE NACA WING-FLOW METHOD. 
James P. Trant, Jr. Jane 1952. 23p. diagrs., 
photos., tab. (NACA RM L52B15a) 



AERODYNAMICS 
STABILITY AND CONTROL (1.8) 



97 



Longitudinal Control fCont. ) 

CONTROL CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A LINKED FLAP AND SPOILER ON A 
TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3. Vernard E. Lockwood and Joseph E. 
Fikes. July 1952. 24p. diagrs., photo. (NACA 
RM L52D25) 

CONTROL EFFECTIVENESS AND HINGE-MOMENT 
CHARACTERISTICS AT LOW SPEED OF LARGE- 
CHORD, HORN-BALANCED, FLAP-TYPE CON- 
TROLS ON A TRIANGULAR WING OF ASPECT 
RATIO 2. Jules B. Dods, Jr. August 1952. 53p. 
diagrs., photos., 2 tabs. (NACA RM A52F13) 

HINGE-MOMENT AND CONTROL-EFFECTIVENESS 
CHARACTERISTICS OF AN OUTBOARD FLAP WITH 
AN OVERHANG NOSE BALANCE ON A TAPERED 
35° SWEPTBACK WING OF ASPECT RATIO 4. 
TRANSONIC -BUMP METHOD. Robert F. Thompson 
and William C. Moseley, Jr. August 1952. 51p. 
diagrs. (NACA RM L52G08^ 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 60° DELTA WING EQUIPPED WITH A 
CONSTANT-CHORD FLAP-TYPE CONTROL WITH 
AND WITHOUT AN UNSHIELDED HORN BALANCE. 
TRANSONIC -BUMP METHOD. Harleth G. Wiley 
and Leon Zontek. September 1952. 25p. diagrs. 
(NACA RM L51H22) 

TESTS OF A CENTERING SPRING USED AS AN AR- 
TIFICAL FEEL DEVICE ON THE ELEVATOR OF A 
FIGHTER AIRPLANE. James J. Adams and James 
B. Whitten. September 1952. 18p. diagrs., photo., 
tab. (NACA RM L52G16) 

INVESTIGATION AT TRANSONIC SPEEDS OF THE 
EFFECT OF A POSITIVE-UFT BALANCING TAB 
ON THE HINGE -MOMENT AND LIFT CHARACTER- 
ISTICS OF A FULL-SPAN FLAP ON A TAPERED 
45° SWEPTBACK WING OF ASPECT RATIO 3. 
Vernard E. Lockwood and Joseph E. Fikes. 
November 1952. 22p. diagrs. , photo. (NACA 
RM L52J09) 

FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW-SPEED STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A MODEL HAVING A FUSELAGE 
OR RELATIVELY FLAT CROSS SECTION. John W. 
Paulson and Joseph L. Johnson, Jr. February 1953. 
30p. diagrs., photo., tab. (NACA EM L52L22) 

INVESTIGATION AT TRANSONIC SPEEDS OF THE 
HINGE-MOMENT AND LIFT-EFFECTIVENESS 
CHARACTERISTICS OF A SINGLE FLAP AND A 
TANDEM FLAP ON A 60° DELTA WING. Delwin 
R. Croom and Harleth G. Wiley. July 1953. 16p. 
diagrs. (NACA RM L53E28a) 

THE EFFECT OF CONTROL-SURFACE-SERVO 
NATURAL FREQUENCY ON THE DYNAMIC PER- 
FORMANCE CHARACTERISTICS OF AN ACCELER- 
ATION CONTROL SYSTEM APPLIED TO A SUPER- 
SONIC MBSILE. Anthony L. Passera and Martin L. 
Nason. September 1953. 28p. diagrs., 3 tabs. 
(NACA RM L53G23a) 

DYNAMIC STABIUTY AND CONTROL CHARACTER- 
ISTICS OF A CASCADE-WING VERTICALLY RISING 
AIRPLANE MODEL IN TAKE-OFFS, LANDINGS, 
AND HOVERING FUGHT. Marion O. McKinney, 
Louis P. Tosti and Edwin E. Davenport. June 1954. 
45p. diagrs., photos., tab. (NACA TN 3198) 

THEORETICAL INVESTIGATION OF LONGITUDINAL 
RESPONSE CHARACTERISTICS OF A SWEPT -WWG 
FIGHTER AIRPLANE HAVING A NORMAL- 
ACCELERATION CONTROL SYSTEM AND A COM- 
PARISON WITH OTHER TYPES OF SYSTEMS. Fred 
H. Stokes and Charles W. Mathews. July 1954. 50p. 
diagrs., tab. (NACA TN 3191) ^ 



THEORETICAL ANALYSIS OF AN AIRPLANE 
ACCELERATION RESTRICTOR CONTROLLED BY 
NORMAL ACCELERATION, PITCHING ACCELERA- 
TION, AND PITCHING VELOCITY. Christopher C. 
Kraft, Jr. September 1954. 42p. diagrs., 3 tabs. 
(NACA TN 3243) 

OPERATING CHARACTERISTICS OF AN 
ACCELERATION RESTRICTOR AS DETERMINED 
BY MEANS OF A SIMULATOR. Arthur 
Assadourian. December 1954. 20p. diagrs., 
photos. (NACA TN 3319) 

GROUND-SIMULATOR STUDY OF THE EFFECTS 
OF STICK FORCE AND DBPLACEMENT ON 
TRACKING PERFORMANCE. Stanley Faber. 
AprU 1955. 21p. diagrs., photos. (HACA TN 3428) 

HOVERING FLIGHT TESTS OF A FOUR-ENGINE- 
TRANSPORT VERTICAL TAKE-OFF AIRPLANE 
MODEL UTILIZING A LARGE FLAP AND EXTEN- 
SIBLE VANES FOR REDIRECTING THE PROPEL- 
LER SLIPSTREAM. Louis P. Tosti and Edwin E. 
Davenport. May 1955. 26p. diagrs., photos., tab. 
(NACA TN 3440) 

LATERAL CONTROL 
(1.8.2.2) 

OBSERVATIONS ON AN AILERON-FLUTTER IN- 
STABILITY ENCOUNTERED ON A 45° SWEPT- 
BACK WING IN TRANSONIC AND SUPERSONIC 
FLIGHT. Marvin Pitkin, William N. Gardner and 
Howard J. Curfman, Jr. April 11, 1947. 23p. 
diagrs., photos. (NACA RM L6L09) 

FLIGHT-TEST MEASUREMENTS OF AILERON CON- 
TROL SURFACE BEHAVIOUR AT SUPERCRITICAL 
MACH NUMBERS. Harvey H. Brown, George A. 
Rathert, Jr. and Lawrence A. Clousing. April 23, 

1947. 26p. diagrs., photos., 2 tabs. (NACA 
RM A7A15) 

GENERAL HANDLING-QUALITIES RESULTS 
OBTAINED DURING ACCEPTANCE FLIGHT TESTS 
OF THE BELL XS-1 AIRPLANE. Walter C. 
Williams, Charles M. Forsyth and Beverly P. 
Brown. April 19, 1948. 72p. diagrs., photos., tab. 
(NACA RM L8A09) 

FACTORS AFFECTING LATERAL STABILITY AND 
CONTROLLABILITY. John P. CampbeU and 
Thomas A. Toll. May 13, 1948. 19p. diagrs. 
(NACA RM L8A28a) 

FREE-FUGHT INVESTIGATION OF THE ROLLING 
EFFECTIVENESS OF A WING-SPaLER ARRANGE- 
MENT AT HIGH SUBSONIC, TRANSONIC, AND 
SUPERSONIC SPEEDS. Carl A. Sandahl. May 17, 

1948. lOp. diagrs., photo. (NACA RM L8A07) 

PRELIMINARY FREfi-FUGHT INVESTIGATION OF 
THE EFFECT OF AIRFOIL SECTION ON AILERON 
ROLLING EFFECTIVENESS AT TRANSONIC AND 
SUPERSONIC SPEEDS. Carl A. Sandahl. June 25, 
1948. 6p. diagrs. (NACA RM L8B26) 

PRELIMINARY INVESTIGATION OF VARIOUS 
AILERONS ON A 42° SWEPTBACK WING FOR 
LATERAL CONTROL AT TRANSONIC SPEEUS. 
Thomas R. Turner, Vernard E. Lockwood and 
Raymond D. Vogler. September 7, 1948. 35p. 
diagrs., photo. (NACA RM L8D21) 

AERODYNAMIC CHARACTERISTICS AT SUBSONIC 
AND TRANSONIC SPEEDS OF A 42.7° SWEPTBACK 
WING MODEL HAVING AN AILERON WITH FIKJiTE 
TRAILING-EDGE THICKNESS. Thomas R. Turner, 
Vernard E. Lockwood and Raymond D. Vogler. 
January 12, 1949. 24p. diagrs., photo. (KACA 
RM L8K02) 



AERODYNAMICS 
98 STABILITY AND CONTROL (1.8) 



Lateral Control (Cont. ) 

FULL-SCALE DJVESTIGATION OF A WING WITH 
THE LEADING EDGE SWEPT BACK 47. 5° AND 
HAVING CIRCULAR -ARC AND FINITE -TR AILING- 
EDGE -THICKNESS AILERONS. RoyH. Lange. 
March 11, 1949. 16p. diagrs., photo. (NACA 
RM L9B02) 

AN EXPERIMENTAL INVESTIGATION OF A GYRO- 
ACTUATED ROLL CONTROL SYSTEM INSTALLED 
IN A SUBSONIC TEST VEHICLE. Jerome M. 
Teitelbaum and Ernest C. Seaberg. April 20, 1949. 
26p. diagrs., photos., tab. (NACA RM L9B24a) 

HIGH-SUBSONIC DAMPING-IN-ROLL CHARACTER. 
ISTICS OF A WING WITH THE QUARTER-CHORD 
LINE SWEPT BACK 35° AND WITH ASPECT RATIO 
3 AND TAPER RATIO 0.6. Boyd C. Myers, n and 
Richard E. Kuhn. May 10, 1949. 21p. diagrs., 
photo., tab. (NACA RM L9C23) 

WIND-TUNNEL INVESTIGATION AT HIGH SUB- 
SONIC SPEEDS OF THE LATERAL -CONTROL 
CHARACTERISTICS OF AN AILERON AND A 
STEPPED SPOILER ON A WING WITH LEADING 
EDGE SWEPT BACK 51.3°. LesUe E. Schneiter 
and John R. Hagerman. June 7, 1949. 34p. diagrs., 
photo. (NACA RM L9D06) 

MEASUREMENTS OF AILERON EFFECTIVENESS 
OF BELL X-1 AIRPLANE UP TO A MACH NUMBER 
OF 0.82. Hubert M. Drake. June 20, 1949. 7p. 
diagrs. (NACA RM L9D13) 

EFFECTS OF MACH NUMBER AND SWEEP ON THE 
DAMPING-IN-ROLL CHARACTERISTICS OF WINGS 
OF ASPECT RATIO 4. Richard E. Kuhn and Boyd 

C. Myers, n. June 27, 1949. 28p. diagrs., photo. 
(NACA RM L9E10) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER - 
CHORD LINE SWEPT BACK 45°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC -BUMP METHOD. Raymond 

D. Vogler. August 15, 1949. 22p. diagrs. (NACA 
RM L9F29a) 

INViSTIGATION OF EXTENSIBLE WING-TIP 
AILERONS ON AN UNTAPERED SEMISPAN WING 
AT 0° AND 45° SWEEPBACK. John R. Hagerman 
and William M. O'Hare. September 20, 1949. 40p. 
diagrs., photo., tab. (NACA RM L9H04) 

WIND-TUNNEL INVESTIGATION AT LOW TRAN- 
SONIC SPEEDS OF THE EFFECTS OF NUMBER OF 
WINGS ON THE LATERAL-CONTROL EFFECTIVE- 
NESS OF AN RM-5 TEST VEHICLE. Harold S. 
Johnson. November 29, 1949. 15p. diagrs., photo., 
tab. (NACA RM L9H16) 

LOW -SPEED INVESTIGATION OF DEFLECTABLE 
WING-TIP AILERONS ON AN UNTAPERED 45° 
SWEPTBACK SEMISPAN WING WITH AND WITHOUT 
AN END PLATE. Jack Fischel and James M. 
Watson. December 14, 1949. 32p. diagrs., photo. 
(NACA RM L9J28) 

THE EFFECT OF TIP TANKS ON THE ROLLING 
CHARACTERISTICS AT HIGH SUBSONIC MACH 
NUMBERS OF A WING HAVING AN ASPECT RATIO 
OF 3 WITH QUARTER-CHORD LINE SWEPT BACK 
35°. Richard E. Kuhn and Boyd C. Myers, H. 
January 17, 1950. 2"^. diagrs., photo., 2 tabs. 
(NACA RM L9J19) 

INVESTIGATION OF EFFECT OF SPAN AND 
SPANWISE LOCATION OF PLAIN AND STEPPED 
SPOILER AILERONS ON LATERAL CONTROL 
CHARACTERISTICS OF A WING WITH LEADING 
EDGE SWEPT BACK 51.3°. Jack Fischel and 
Alexander D. Hammond. January 18, 1950. 59p. 
diagrs., photos. (NACA RM L9K02) 



LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER- 
CHORD LINE SWEPT BACK 35°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC-BUMP METHOD. Robert F. 
Thompson. January 25, 1950. 22p. - diagrs., tab. 
(NACA RM L9L12a) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH QUARTER- 
CHORD LINE SWEPT BACK 60°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC-BUMP METHOD. Raymond 

D. Vogler. March 2, 1950. 21p. diagrs. (NACA 
RM L50A17) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE CONTROLS ON A WING WITH UNSWEPT 
QUARTER-CHORD LINE, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. TRANSONIC-BUMP METHOD. 
Alexander D. Hammond. March 10, 1950. 20p. 
diagrs. (NACA RM L50A03) 

FLIGHT INVESTIGATION OF THE EFFECT OF 
THICKENING THE AILERON TRAILING EDGE ON 
CONTROL EFFECTIVENESS FOR SWEPTBACK 
TAPERED WINGS HAVING SHARP- AND ROUND- 
NOSE SECTIONS. H. Kurt Strass and Edison M. 
Fields. May 2, 1950. 20p. diagrs., photo., tab. 
(NACA RM L9L19) 

AERODYNAMIC AND LATERAL-CONTROL CHAR- 
ACTERISTICS OF A 1/28-SCALE MODEL OF THE 
BELL X-1 AIRPLANE WING-FUSELAGE COMBINA- 
TION. TRANSONIC -BUMP METHOD. Vernard E. 
Lockwood. May 5, 1950. 28p. diagrs., tab. (NACA 
RM L50C22) 

FLIGHT INVESTIGATION OF THE AILERON CHAR- 
ACTERISTICS OF THE DOUGLAS D-558-I AIR- 
PLANE (BUAERO NO. 37972) AT MACH NUMBERS 
BETWEEN 0.6 AND 0.89. Jim Rogers Thompson, 
William S. Roden and John M. Eggleston. May 26, 
1950. 23p. diagrs., photos., tab. (NACA 
RM L50D20) 

STABILITY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LATERAL AND DIRECTIONAL STABILITY 
AND CONTROL. William B. Kemp, Jr. and Robert 

E. Becht. June 20, 1950. 97p. diagrs., photos. 
(NACA RM L50C17a) 

LATERAL-CONTROL INVESTIGATION OF FLAP- 
TYPE AND SPOILER -TYPE CONTROLS ON A WING 
WITH QUARTER -CHORD-LINE SWEEPBACK OF 
60°, ASPECT RATIO 2, TAPER RATIO 0.6, AND 
NACA 65A006 AIRFOIL SECTION. TRANSONIC- 
BUMP METHOD. Alexander D. Hammond. July 18, 
1950. 26p. diagrs. (NACA RM L50E09) 

INVESTIGATION OF FLAP -TYPE AILERONS ON AN 
UNTAPERED WING HAVING AN ASPECT RATIO OF 
3.7, 45° SWEEPBACK, AND AN NACA 65A009 AIR- 
FOIL SECTION. TRANSONIC -BUMP METHOD. 
Richard G. MacLeod. August 23, 1950. 18p. 
diagrs. (NACA RM L50G03) 

INVESTIGATION AT TRANSONIC SPEEDS OF A 
35-PERCENT-CHORD AILERON ON A TAPERED 
WEDGE-TYPE WING OF ASPECT RATIO 2.5 WITH 
AND WITHOUT A FISELAGE. Thomas R. Turner 
and Joseph E. Fikes. September 8, 1950. 25p. 
diagrs. (NACA RM L50G13a) 

PRELIMINARY FLIGHT INVESTIGATION OF THE 
WING-DROPPING TENDENCY AND LATERAL- 
CONTROL CHARACTERISTICS OF A 35° SWEPT- 
WING AIRPLANE AT TRANSONIC MACH NUMBERS. 
George A. Rathert, Jr. , L. Stewart Rolls, Lee 
Winograd and George E. Cooper. September 11, 
1950. 14p. diagrs., photo., tab. (NACA RM A50H03) 



AERODYNAMICS 
STABILITY AND CONTROL (1.8) 



99 



Lateral Control (Cont. ) 

LOW-SPEKD INVESTIGATION OF THE^FFECT OF 
SEVERAL FLAP AND SPOILER AILERONS ON THE 
LATERAL CHARACTERISTICS OF A 47.5° 
SWEPTBACK-WING - FUSELAGE COMBINATION 
AT A REYNOLDS NUMBER OF 4.4 x lO^. Jerome 
Fasamanick and Thomas B. Sellers. December 8, 
1950. 57p. diagrs., photo. (NACA RM L50J20) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 60° DELTA WING EQUIPPED WITH A 
TRIANGULAR PLAN-FOKM CONTROL HAVING A 
SKEWED HINGE AXIS AND AN OVERHANG BAL- 
ANCE. TRANSONIC-BUMP METHOD. Harleth G. 
Wiley. February 6, 1951. 31p. diagrs. (NACA 
RM L50L01) 

THE EFFECT OF MASS DISTRIBUTION ON THE 
LOW-SPEED DYNAMIC LATERAL STABILITY AND 
CONTROL CHARACTERISTICS OF A MODEL WITH 
A 60° TRIANGULAR WING. Joseph L. Johnson. 
March 9, 1951. 23p. diagrs., 2 tabs. (NACA 
RM L50K10) 

LOW -SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AffiPLANE - LATERAL AND 
DIRECTIONAL CHARACTERISTICS. Noel K. Delany 
and Nora-Lee F. Hayter. March 16, 1951. 56p. 
diagrs., photos., tab. (RM A51A16) 

FLIGHT MEASUREMENTS OF THE WING- 
DROPPING TENDENCY OF A STRAIGHT -WING JET 
AIRPLANE AT HIGH SUBSONIC MACH NUMBERS. 
Seth B. Anderson, Edward A. Ernst and Rudolph D. 
Van Dyke, Jr. April 24, 1951. 16p. diagrs., photo., 
tab. (NACA RM A51B28) 

EFFECT OF A DEFLECTABLE WING-TIP CON- 
TROL ON THE LOW-SPEED LATERAL AND 
LONGITUDINAL CHARACTERISTICS OF A LARGE- 
SCALE WING WITH THE LEADING EDGE SWEPT 
BACK 47.5°. Roy H. Lange and Marvin P. Fink. 
April 26, 1951. 41p. diagrs., photo., 2 tabs. 
(NACA RM L51C07) 

AERODYNAMIC CHARACTERISTICS AT TRAN- 
SONIC SPEEDS OF A TAPERED 45° SWEPTBACK 
WING OF ASPECT RATIO 3 HAVING A FULL-SPAN 
FLAP-TYPE CONTROL. TRANSONIC -BUMP 
METHOD. Vernard E. Lockwood and Joseph E. 
Fikes. August 1951. 35p. diagrs. (NACA 
RM L51F06a) 

AN INVESTIGATION AT TRANSONIC SPEEDS OF 
THE EFFECTS OF CONTROL CHORD AND SPAN 
ON THE CONTROL CHARACTERISTICS OF A 
TAPERED WEDGE -TYPE WING OF ASPECT RATIO 
2.5. TRANSONIC -BUMP METHOD. Raymond D. 
Vogler, Vernard E. Lockwood and Thomas R. 
Turner. September 1951. 36p. diagrs. (NACA 
RM L51G03) 

STABILITY AND CONTROL MEASUREMENTS OB- 
TAINED DURING USAF-NACA CGOPERATIVE 
FLIGHT-TEST PROGRAM ON THE X-4 AIRPLANE 
(USAF NO. 46-677). Melvin Sadoff, Herman O. 
Ankenbruck and William O'Hare. October 1951. 38p. 
diagrs., photos., tab. (NACA RM A51H09) 

INVESTIGATION OF WING-TIP AILERONS ON A 
51.3° SWEPTBACK WING AT TRANSONIC SPEEDS 
BY THE TRA^BONIC-BUMP METHOD; WilUam C. 
Moseley, Jr. and James M. Watson. November 1951. 
60p. diagrs. (NACARM L51H27) 

THE EFFECT OF RAKING THE AILERON TIPS ON 
THE LATERAL -CONTROL AND HINGE-MOMENT 
CHARACTERKTICS OF A 20-PERCENT-CHORD 
PARTIAL-SPAN OUTBOARD AILERON ON A WING 
WITH LEADING EDGE SWEPT BACK 51.3°. 
Alexander D. Hammond. November 1951. 41p. 
diagrs., photo., tab. (NACA RM L51H29) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A TAPERED 45° SWEPTBACK WING 
OF ASPECT RATIO 3 HAVING A FULL-SPAN FLAP 
TYPE OF CONTROL WITH OVERHANG BALANCE. 
TRANSONIC -BUMP METHOD. Vernard E. 
Lockwood and John R. Hagerman. January 1952. 
24p. diagrs. (NACA RM L51L11) 

THE EFFECTIVENESS OF WING VORTEX GENER- 
ATORS IN IMPROVING THE MANEUVERING CHAR- 
ACTERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, George 
A. Rathert, Jr. and Richard S. Bray. February 1952. 
45p. photos., diagrs., tab. (NACA RM A51J18) 

LOW-SPEED WIND-TUNNEL INVESTIGATION OF A 
FIXED AND A FREE-FLOATING WDJG-TIP AILER- 
ON ON A WING WITH LEADING EDGE SWEPT 
BACK 51.3°. R. G. MacLeod. February 1952. 
17p. diagrs., photo., tab. (NACA RM L51H16a) 

PRELIMINARY INVESTIGATION OF THE EFFECTS 
OF A PADDLE BALANCE ON THE CONTROL 
CHARACTERBTICS AT TRANSONIC SPEEDS OF A 
TAPERED 45.580 SWEPTBACK WING OF ASPECT 
RATIO 3 HAVING A FULL-SPAN FLAP-TYPE CON- 
TROL. William C. Moseley, Jr. February 1952. 
24p. diagrs., photo. (NACA RM L51L19) 

HINGE -MOMENT AND OTHER AERODYNAMIC 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
QUARTER-SPAN SPOILER ON A TAPERED 45° 
SWEPTBACK WING OF ASPECT RATIO 3. 
Joseph E. Fikes. February 1952. 22p. diagrs., 
photo. (NACA RM L52A03) 

PRELIMINARY INVESTIGATION OF CONTROL 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3 HAVING A HORN-BALANCED FULL-SPAN 
CONTROL. John G. Lowry and Joseph E. Fikes. 
April 1952. 22p. diagrs., photo. (NACA RM 
L52A11) 

PRELIMINARY INVESTIGATION AT TRANSONIC 
SPEEDS OF THE EFFECT OF BALANCING TABS 
ON THE HINGE-MOMENT AND OTHER AERODY- 
NAMIC CHARACTERISTICS OF A FULL-SPAN FLAP 
ON A TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3. Vernard E. Lockwood and Joseph E. 
Fikes. April 1952. 27p. diagrs., photo., (NACA 
RM L52A23) 

CONTROL CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A LINKED FLAP AND SPOILER ON A 
TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3. Vernard E. Lockwood and Joseph E. 
Fikes. July 1952. 24p. diagrs., photo. (NACA 
RM L52D25) 

THE CALCULATION OF CERTAIN STATIC AERO- 
ELASTIC PHENOMENA OF WDKS WITH TIP 
TANKS OR BOOM-MOUNTED LIFTING SURFACES. 
Franklin W. Diederich and Kenneth A. Foss. 
August 1952. 55p. diagrs., 2 tabs. (NACA 
RM L52A22^ 

LATERAL-CONTROL INVESTIGATION AT TRAN- 
SONIC SPEEDS OF RETRACTABLE SPOILER AND 
PLUG-TYPE SPOILER-SLOT AILERONS ON A 
TAPERED 60° SWEPTBACK WING OF ASPECT 
RATIO 2. TRANSONIC -BUMP METHOD. Alexander 
D. Hammond and James M. Watson. August 1952. 
19p. diagrs. (NACA RM L52F16) 

HINGE-MOMENT AND CONTROL-EFFECTIVENESS 
CHARACTERISTICS OF AN OUTBOARD FLAP WITH 
AN OVERHANG NOSE BALANCE ON A TAPERED 
35° SWEPTBACK WING OF ASPECT RATIO 4. 
TRANSONIC -BIMP METHOD. Robert F. Thompson 
and William C. Moseley, Jr. August 1952. 51p. 
diagrs. (NACA RM L52G08) 



AKRODYNAMICS 
.100 STABILITY AND CONTROL (1.8) 



Lateral Control (Cont. ) 

PtrGHTMEASfai'EMENTS OF TBE LATERAL "STa- 
BILmf AND CONTROL CHARACTERISTICS OF A 
HIGH-SPEED FICaiTER AIRPLANE. H. L. Crane, 
A. R. Beckhardt and C. E. MathPny. September 
1952. 50p. diagrs., tab. (NACA RM L52B14) 

THE EFFECT OF VARIOUS AERODYNAMIC BAL- 
ANCES ON THE LOW-SPEED LATERAL-CONTROL 
AND HINGE-MOMENT CHARACTERISTICS OF A 
0.20-CHORD PARTIAL-SPAN OUTBOARD AILERON 
ON A WING WITH LEADING EDGE SWEPT BACK 
51.3°. Alexander D. Hammond. September 1952. 
40 p. diagrs., photo., tab. (NACA RM L52G03) 

LOW -SPEED LATERAL-CONTROL INVESTIGATION 
OF A FLAP -TYPE SPOILER AILERON WITH AND 
WITHOUT A DEFLECTOR AND SLOT ON A 6- 
PERCENT-THICK, TAPERED, 45° SWEPTBACK 
WING OF ASPECT RATIO 4. James M. Watson. 
September 1952. lip. diagrs. (NACA RM L52G10) 

A WIND-TUNNEL INVESTIGATION AT LOW 
SPEEDS OF THE AERODYNAMIC CHARACTER- 
ISTICS OF VARIOUS SPOILER CONFIGURATIONS 
ON A THIN 60° DELTA WING. Harleth G. Wiley 
and Martin Solomon. November 1952. 20p. diagrs. 
(NACA RM L52J13) 

LATERAL AND DIRECTIONAL DYNAMIC - 
RESPONSE CHARACTERISTICS OF A 35° SWEPT- 
WING AIRPLANE AS DETERMINED FROM FLIGHT 
MEASUREMENTS. William C. Triplet! and 
Stuart C. Brown. December 1952. 62p. diagrs., 
photo., 3 tabs. (NACA RM A52I171 

CHARACTERISTICS OF FLAP-TYPE SPOILER 
AILERONS AT VARIOUS LOCATIONS ON A 60° 
DELTA WING WITH A DOUBLE SLOTTED FLAP. 
Delwin R. Croom. December 1952. 31p. diagrs., 
3 tabs. (NACA RM L52J24) 

THE EFFECTS ON DYNAMIC LATERAL STABILITY 
AND CONTROL OF LARGE ARTIFICIAL VARIA- 
TIONS IN THE ROTARY STABILITY DERIVATIVES. 
Robert O. Schade and James L. Hassell, Jr. 1953. 
ii, 24p. diagrs., photo., 2 tabs. (NACA Rept. 1151. 
Formerly TN 2781) 

INVESTIGATION AT TRANSONIC SPEEDS OF THE 
HINGE-MOMENT AND LIFT-EFFECTIVENESS 
CHARACTERISTICS OF A SINGLE FLAP AND A 
TANDEM FLAP ON A 60° DELTA WING. Delwln 
R. Croom and Harleth G. Wiley. July 1953. 16p. 
diagrs. (NACA RM L53E28a) 

LOW-SPEED INVESTIGATION OF THE LATERAL 
CONTROL CHARACTERISTICS OF THREE TIP AIL- 
ERONS ON A 60° TRIANGULAR WING. Stanley M. 
Gottlieb. August 1953. 24p. diagrs., photo. (NACA 
RM L53F16a) 

METHOD FOR CALCULATING THE ROLLING AND 
YAWING MOMENTS DUE TO ROLLING FOR UN- 
SWEPT WINGS WITH OR WITHOUT FLAPS OR 
AILERONS BY USE OF NONLINEAR SECTION LIFT 
DATA. Albert P. Martina. 1954. ii, 16p. diagrs., 
11 tabs, (NACA Rept. 1167. Formerly TN 2937) 

DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A CASCADE-WING VERTICALLY RISING 
AIRPLANE MODEL IN TAKE-OFFS, LANDINGS, 
AND HOVERING FLIGHT. Marion O. McKinney, 
Louis P. Tosti and Edwin E. Davenport. June 1954. 
45p. diagrs., photos., tab. (NACA TN 3198) 

A SIMPLIFIED METHOD FOR CALCULATING 
AEROELASTIC EFFECTS ON THE ROLL OF AIR- 
CRAFT. John M. Hedgepeth, Paul G. Waner, Jr. 
and Robert J. Keil. March 1955. 26p. diagrs., 
4 tabs. (NACA TN 3370) 



HOVERING FLIGHT TESTS OF A FOUR-ENGINE- 
TRANSPORT VERTICAL TAKE-OFF AIRPLANE 
MODEL UTILIZING A LARGE FLAP AND EXTEN- 
SIBLE VANES FOR REDIRECTING THE PROPEL- 
LER SLIPSTREAM. Louis P. Tosti and Edwin E. 
Davenport. May 1955. 26p. diagrs., photos., tab. 
(NACA TN 3440) 

DIRECTIONAL CONTROL 
(1.8.2.3) 

WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 1.53 OF AN AIRPLANE WITH A TRIANGU- 
LAR WING. Richard Scherrer and William R. 
Wimbrow. January 23, 1948. 74p. diagrs., 
photos., 2 tabs. (NACA RM A7J05) 

GENERAL HANDLING-QUALITIES RESULTS 
OBTAINED DURING ACCEPTANCE FUGHT TESTS 
OF THE BELL XS-1 AIRPLANE. Walter C. 
Williams, Charles M. Forsyth and Beverly P. 
Brown. April 19, 1948. 72p. diagrs., photos., tab. 
(NACA RM L8A09) 

FACTORS AFFECTING LATERAL STABILITY AND 
CONTROLLABILITY. John P. CampbeU and 
Thomas A. Toll. May 13, 1948. 19p. diagrs. 
(NACA RM L8A28a) 

STABIUTY AND CONTROL CHARACTERISTICS AT 
LOW SPEED OF A 1/4-SCALE BELL X-5 AIRPLANE 
MODEL. LATERAL AND DIRECTIONAL STABILITY 
AND CONTROL. William B. Kemp, Jr. and Robert 
E. Becht. June 20, 1950. S7p. diagrs., photos. 
(NACA RM L50C17a) 

PRELIMINARY FLIGHT INVESTIGATION OF THE 
WING-DROPPING TENDENCY AND LATERAL- 
CONTROL CHARACTERISTICS OF A 35° SWEPT- 
WING AIRPLANE AT TRANSONIC MACH NUMBERS. 
George A. Rathert, Jr. , L. Stewart Rolls, Lee 
Winograd and George E. Cooper. September 11, 
1950. 14p. diagrs., photo., tab. (NACA RM A50H03) 

LOW -SPEED INVESTIGATION OF A 0.16-SCALE 
MODEL OF THE X-3 AIRPLANE - LATERAL AND 
DIRECTIONAL CHARACTERISTICS. Noel K. Delany 
and Nora-Lee F. Hayter. March 16, 1951. 56p. 
diagrs., photos., tab. (RM A51A16) 

CONTROL EFFECTIVENESS AND HINGE -MOMENT 
CHARACTERISTICS AT LOW SPEED OF LARGE- 
CHORD, HORN-BALANCED,, FLAP-TYPE CON- 
TROLS ON A TRIANGULAR WING OF ASPECT 
RATIO 2. Jules B. Dods, Jr. August 1952. 53p. 
diagrs., photos., 2 tabs. (NACA RM A52F13) 

FUGHT MEASUREMENTS OF THE LATERAL STA- 
BILITY AND CONTROL CHASACTEHSTICS OF A 
HIGH-SPEED FICaiTER AIRPLANE. H. L. Crane, 
A. R. Beckhardt and C. E. Matheny. September 
1952. 50p. diagrs., tab. (NACA RM L52B14) 

LATERAL AND DIRECTIONAL DYNAItfllC- 
RESPONSE CHARACTERBTICS OF A 35° SWEPT- 
WING AIRPLANE AS DETERMINED FROM FLIGHT 
MEASUREMENTS. William C. Triplett and 
Stuart C. Brown. December 1952. 62p. diagrs., 
photo., 3 tabs. (NACA RM A52I17) 

THE EFFECTS ON DYNAMIC LATERAL STABILITY 
AND CONTROL OF LARGE AHTIFICIAL VARIA- 
TIONS IN THE ROTARY STABILITY DERIVATIVES. 
Robert O. Schade and James L. Hassell, Jr. 1953. 
Ii, 24p. diagrs., photo., 2 tabs. (NACA Hept. 1151. 
Formerly TN 2TO1) 

FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW -SPEED STABILITY AKB CONTROL CHAR- 
ACTERISTICS OF A MODEL HAVING A FUSELAGE 
OR RELATIVELY FLAT CHOSS SECTION. John W. 
Paulson and Joseph L. Johnson, Jr. February 1953. 
30p. diagrs., photo., tab. (NACA RM L52L22) 



AERODYNAMICS 
STABILITY AND CONTROL. (1. 8) 



101 



Directional Control (Cont. ) 

DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A CASCADE-WING VERTICALLY RISING 
AIRPLANE MODEL IN TAKE-OFFS, LANDINGS, 
AND HOVERING FLIGHT. Marion O. McKinney, 
Louis P. Tosti and Edwin E. Davenport. June 1954. 
45p. diagrs., photos., tab. (NACATN3198) 

STEADY PROPERLY-BANKED TURNS OF 
TURBOJET-PROPELLED AIRPLANES. (La Virata 
Corretta Stazlonaria Degli Aeroplanl Azlonati da 
Turboreattorl). Angelo Miele. March 1955. 33p. 
diagrs., tab. (NACA TM 1382. Trans, from Rivista 
Aeronautica, v.27, no.l, 1951, p.23-35) 



HOVERING FLIGHT TESTS OF A FOUR-ENGINE- 
TRANSPORT VERTICAL TAKE-OFF AIRPLANE 
MODEL UTILIZING A LARGE FLAP AND EXTEN- 
SIBLE VANES FOR REDIRECTING THE PROPEL- 
LER SLIPSTREAM. Louis P. Tosti and Edwin E. 
Davenport. May 1955. 26p. diagrs., photos., tab. 
(NACA TN 3440) 



HINGE' MOMENTS 
(1.8.2. 5) 



FUGHT-TEST MEASUREMENTS OF AILERON CON- 
TROL SURFACE BEHAVIOUR AT SUPERCRITICAL 
MACH NUMBERS. Harvey H. Brown, George A. 
Rathert, Jr. and Lawrence A. dousing. April 23, 
1947. 26p. diagrs., photos., 2 tabs. (NACA 
RM A7A15) 



HIGH-SPEED WIND-TUNNEL TESTS OF A MODEL 
PURSUIT AIRPLANE AND CORRELATION WITH 
FLIGHT -TEST RESULTS. Joseph W. Cleary and 
Lyle J. Gray. January 21, 1948. 56p. diagrs., 
photos. (NACA RM A7I16) 



MEASUREMENTS OF AERODYNAMIC CHARACTER- 
ISTICS OF A 35° SWEPTBACK NACA 65-009 AIR- 
FOIL MODEL WITH 1/4-CHORD HORN-BALANCED 
FLAP BY THE NACA WING-FLOW METHOD. 
Harold I. Johnson and B. Porter Brown. April 18, 
1949. 59p. diagrs., photo. (NACA RM L9B23a) 



AIR BRAKES 
(1.8.2.4) 



HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE. D-558-1 SPEED-REDUCTION BRAKE 
AND SYMMETRICAL-PROFILE WING CHARACTER- 
ISTICS. John B. Wright. June 15, 1948. 22p. 
diagrs., tab. (NACA RM L8B06) 



FORCE, STATIC LONGITUDMAL STABILITY, AND 
CONTROL CHARACTERISTICS OF A 1/16-SCALE 
MODEL OF THE BELL XS-1 TRANSONIC RE- 
SEARCH AIRPLANE AT HIGH MACH NUMBERS. 
Axel T. Mattson and Donald L. Loving. June 23, 
1948. 49p. diagrs., tab. (NACA RM L8A12) 



STABILITY CHARACTERISTICS AT LOW SPEED OF 
A 1/4-SCALE BELL X-5 AIRPLANE MODEL WITH 
VARIOUS MODIFICATIONS TO THE BASIC MODEL 
CONFIGURATIONS. Roberta. Becht and Albert G. 
Few, Jr. August 16, 1950. 47p. diagrs., photo. 
(NACA RM L50F23) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AT HIGH-SUBSONIC SPEEDS OF TWO 
MODELS OF A TRANSONIC RESEARCH AIRPLANE 
WITH WINGS AND HORIZONTAL TAILS OF ASPECT 
RATIOS 4.2 AND 2. Arvo A. Luoma and John B. 
Wright. September 29, 1950. 134p. diagrs., photos., 
3 tabs. (NACA RM L50H07) 



STABILITY AND CONTROL CHARACTERISTICS OF 
A 1/4-SCALE BELL S-5 AIRPLANE MODEL IN 
THE LANDING CONFIGURATION. Robert E. Becht. 
December 18, 1950. 38p. diagrs., photos. (NACA 
RM L50J27) 



EFFECTS OF A FUSELAGE FLAP DIVE BRAKE ON 
THE AERODYNAMIC CHARACTERISTICS OF 1/30- 
SCALE SEMBPAN MODEL OF THE BELL X-5 
VARIABLE -SWEEP AIRPLANE AT A MACH NUM- 
BER 1.24 AS DETERMINED BY THE NACA WING- 
FLOW METHOD. Robert M. Kennedy. February 8, 
1951. 15p. diagrs., photos., tab. (NACA 
RM L50Llla) 



WIND-TUNNEL INVESTIGATION AT HIGH SUB- 
SONIC SPEEDS OF THE LATERAL -CONTROL 
CHARACTERISTICS OF AN AILERON AND A 
STEPPED SPOILER ON A WING WITH LEADING 
EDGE SWEPT BACK 51. 3°. LesUe E. Schneiter 
and John R. Hagerman. June 7, 1949. 34p. diagrs., 
photo. (NACA RM L9D06) 



MEASUREMENTS OF AERODYNAMIC CHARACTER- 
ISTICS OF A 35° SWEPTBACK NACA 65-009 AIR- 
FOIL MODEL WITH 1/4-CHORD BEVELLED- 
TRAILING-EDGE FLAP AND TRIM TAB BY THE 
NACA WING-FLOW METHOD. Harold L Johnson 
and B. Porter Brown. January 6, 1950. 68p. 
diagrs., photo. (NACA RM L9K11) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF A 
45° SWEPTBACK HORIZONTAL TAIL WITH PLAIN 
AND HORN-BALANCED CONTROL SURFACES. 
Harold S. Johnson and Robert F. Thompson. 
March 31, 1950. 44p. diagrs., photo., tab. (NACA 
RM L50B13) 



FLIGHT INVESTIGATION OF THE AILERON CHAR- 
ACTER3BTICS OF THE DOUGL^ D-558-1 AIR- 
PLANE (BUAERO NO. 37972) AT MACH NUMBERS 
BETWEEN 0.6 AND 0.89. Jim Rogers Thompson, 
William S. Roden and John M. Eggleston. May 26, 
1950. 23p. diagrs., photos., tab. (NACA 
RM L5QD20) 



MEASUREMENTS OF AERODYNAMIC CHARACTER- 
ISTICS OF A 35° SWEPTBACK NACA 65-009 AIR- 
FOIL MODEL WITH 1/4-CHORD FLAP HAVING A 
31-PERCENT-FLAP-CHORD OVERHANG BALANCE 
BY THE NACA WING-FLOW METHOD. Harold L 
Johnson and Harold R. Goodman.' September 25, 
1950. 38p. diagrs., photo. (NACA RM L50H09) 



WIND-TUNNEL INVESTIGATION AT MACH 
NUMBERS FROM 0.50 TO 1.29 OF AN UNSWEPT 
TAPERED WING OF ASPECT RATIO 2.67 WITH 
LEADING- AND TRAILING-EDGE FLAPS - 
TRAILING-EDGE FLAPS DEFLECTED. Louis S. 
Stivers, Jr. and Alexander W. Malick. 
December 13, 1950. 45p. diagrs., photo., 5 tabs. 
(NACA RM A50J09b) 



102 STABILITY 



AERODYNAMICS 

AND CONTROL, (1.8) 



Hinge Moments - Control (Cont. ) 

INVESTIGATION OF A 42.7° SWEPTBACK WING 
MODEL TO DETERMINE THE EFFECTS OF 
TRAILING-EDGE THICKNESS ON THE AILERON 
HINGE-MOMENT AND FLUTTER CHARACTER- 
ISTICS AT TRANSONIC SPEEDS. Robert F. 
Thompson. December 26, 1950. 42p. diagrs., 
photos., 2 tabs. (NACA RM L50J06) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 60° DELTA WING EQUIPPED WITH A 
TRIANGULAR PLAN-FORM CONTROL HAVING A 
SKEWED HINGE AXIS AND AN OVERHANG BAL- 
ANCE. TRANSONIC -BUMP METHOD. Harleth G. 
Wiley. February 6, 1951. 31p. diagrs. (NACA 
RM L50L01) 

WIND-TUNNEL INVESTIGATION AT MACH NUM- 
BERS FROM 0.50 TO 1.29 OF AN UNSWEPT, 
TAPERED WING OF ASPECT RATIO 2.67 WITH 
LEADING- AND TRAILING-EDGE FLAPS - 
LEADING-EDGE FLAPS DEFLECTED. Louis S. 
Stivers, Jr. and Alexander W. Malick. February 26, 
1951. 37p. diagrs., photo., 5 tabs. (NACA 
RM A50K10) 

AERODYNAMIC CHARACTERISTICS AT TRAN- 
SONIC SPEEDS OF A TAPERED 45° SWEPTBACK 
WING OF ASPECT RATIO 3 HAVING A FULL-SPAN 
FLAP-TYPE CONTROL. TRANSONIC-BUMP 
METHOD. Vernard E. Lockwood and Joseph E. 
Fikes. August 1951. 35p. diagrs. (NACA 
RM L51F06a) 

THE EFFECT OF RAKING THE AILERON TIPS ON 
THE LATERAL-CONTROL AND HINGE-MOMENT 
CHARACTERISTICS OF A 20-PERCENT-CHORD 
PARTIAL-SPAN OUTBOARD AILERON ON A WING 
WITH LEADING EDGE SWEPT BACK 51.3°. 
Alexander D. Hammond. November 1951. 41p. 
diagrs., photo., tab. (NACA RM L51H29) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A TAPERED 450 SWEPTBACK WING 
OF ASPECT RATIO 3 HAVING A FULL-SPAN FLAP 
TYPE OF CONTROL WITH OVERHANG BALANCE. 
TRANSONIC -BUMP METHOD. Vernard E. 
Lockwood and John R. Hagerman. January 1952. 
24p. diagrs. (NACA RM L51L11) 



PRELIMINARY INVESTIGATION OF THE EFFECTS 
OF A PADDLE BALANCE ON THE CONTROL 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
TAPERED 45.58° SWEPTBACK WING OF ASPECT 
RATIO 3 HAVING A FULL-SPAN FLAP-TYPE CON- 
TROL. William C. Moseley, Jr. February 1952. 
24p. diagrs., photo. (NACA RM L51L19) 

HINGE -MOMENT AND OTHER AERODYNAMIC 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
QUARTER-SPAN SPOILER ON A TAPERED 45° 
SWEPTBACK WING OF ASPECT RATIO 3. 
Joseph E. Fikes. February 1952. 22p. diagrs., 
photo. (NACA RM L52A03) 

PRELIMINARY INVESTIGATION OF CONTROL 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3 HAVING A HORN-BALANCED FULL-SPAN 
CONTROL. John G. Lowry and Joseph E. Fikes. 
April 1952. 22p. diagrs., photo. (NACA RM 
L52A11) 



PRELIMINARY INVESTIGATION AT TRANSONIC 
SPEEDS OF THE EFFECT OF BALANCING TABS 
ON THE HINGE-MOMENT AND OTHER AERODY- 
NAMIC CHARACTERISTICS OF A FULL-SPAN FLAP 
ON A TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3. Vernard E. Lockwood and Joseph E. 
Fikes. April 1952. 27p. diagrs., photo., (NACA 
RM L52A23) 

AN INVESTIGATION OF LONGITUDINAL CONTROL 
CHARACTERISTICS OF A WING-TIP CONTROL 
SURFACE ON A SWEPTBACK WING AT TRANSONIC 
SPEEDS BY THE NACA WING-FLOW METHOD. 
James P. Trant, Jr. June 1952. 23p. diagrs., 
photos., tab. (NACA RM L52Bl5a) 

CONTROL CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A LINKED FLAP AND SPOILER ON A 
TAPERED 45° SWEPTBACK WING OF ASPECT 
RATIO 3. Vernard E. Lockwood and Joseph E. 
Fikes. July 1952. 24p. diagrs., photo. (NACA 
RM L52D25) 

CONTROL EFFECTIVENESS AND HINGE-MOMENT 
CHARACTERISTICS AT LOW SPEED OF LARGE - 
CHORD, HORN-BALANCED, FLAP-TYPE CON- 
TROLS ON A TRIANGULAR WING OF ASPECT 
RATIO 2. Jules B. Dods, Jr. August 1952. 53p. 
diagrs., photos., 2 tabs. (NACA RM A52F13) 

HINGE -MOMENT AND CONTROL-EFFECTIVENESS 
CHARACTERBTICS OF AN OUTBOARD FLAP WITH 
AN OVERHANG NOSE BALANCE ON A TAPERED 
35° SWEPTBACK WING OF ASPECT RATIO 4. 
TRANSONIC -BUMP METHOD. Robert F. Thompson 
and William C. Moseley, Jr. August 1952. 51p. 
diagrs. (NACA RM L52G08) 

AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 60° DELTA WING EQUIPPED WITH A 
CONSTANT -CHORD FLAP-TYPE CONTROL WITH 
AND WITHOUT AN UNSHIELDED HORN BALANCE. 
TRANSONIC -BUMP METHOD. Harleth G. Wiley 
and Leon Zontek. September 1952. 25p. diagrs. 
(NACA RM L51H22) 

FLIGHT MEASUREMENTS OF THE LATERAL STA- 
BILITY AND CONTROL CHARACTERISTICS OF A 
HIGH-SPEED FICaaTER AIRPLANE. H. L. Crane, 
A. R. Beckhardt and C. E. Matheny. September 
1952. 50p. diagrs., tab. (NACA RM L52B14) 

THE EFFECT OF VARIOUS AERODYNAMIC BAL- 
ANCES ON THE LOW-SPEED LATERAL-CONTROL 
AND HINGE -MOMENT CHARACTERISTICS OF A 
0.20-CHORD PARTIAL-SPAN OUTBOARD AILERON 
ON A WING WITH LEADING EDGE SWEPT BACK 
51.3°. Alexander D. Hammond. September 1952. 
40 p. diagrs., photo., tab. (NACA RM L52G03) 

INVESTIGATION AT TRANSONIC SPEEDS OF THE 
EFFECT OF A POSITIVE-LIFT BALANCING TAB 
ON THE HINGE -MOMENT AND LIFT CHARACTER- 
ISTICS OF A FULL-SPAN FLAP ON A TAPERED 
45° SWEPTBACK WING OF ASPECT RATIO 3. 
Vernard E. Lockwood and Joseph E. Fikes. 
November 1952. 22p. diagrs. , photo. (NACA 
RM L52J09) 

MEASUREMENTS OF AERODYNAMIC CHAR- 
ACTERISTICS AT TRANSONIC SPEEDS OF AN 
UNSWEPT AND UNTAPERED NACA 65-009 AIR- 
FOIL MODEL OF ASPECT RATIO 3 WITH 1/4- 
CHORD PLAIN FLAP BY THE NACA WDJG-FLOW 
METHOD. Harold I. Johnson. June 1953. 35p. 
diagrs., photo. (NACA RM L53D21) 



AERODYNAMICS 

STABILITY AND CONTROL (1.8) 



103 



Hinge Moments - Control (Cont. ) 



EFFECTS OF RATE OF FLAP DEFLECTION ON 
FLAP HINGE MOMENT AND WING LIFT THROUGH 
THE MACH NUMBER RANGE FROM 0.32 TO 0.87. 
Thomas R. Turner. June 1953. 29p. dlagrs., 
photos. (NACA RM L53E11) 

tNATESTIGATION AT TRANSONIC SPEEDS OF THE 
HINGE-MOMENT AND LIFT-EFFECTIVENESS 
CHARACTERISTICS OF A SINGLE FLAP AND A 
TANDEM FLAP ON A 60° DELTA WING. Delwln 
R. Groom and Harleth G. Wiley. July 1953. 16p. 
diagrs. (NACA RM L53E28a) 

LOW -SPEED INVESTIGATION OF THE LATERAL 
CONTROL CHARACTERISTICS OF THREE TIP AIL- 
ERONS ON A 60° TRIANGULAR WING. Stanley M. 
Gottlieb. August 1953. 24p. dlagrs., photo. (NACA 
RM L53F16a) 



THE AERODYNAMIC CHARACTERISTICS AT 
TRANSONIC SPEEDS OF AN ALL-MOVABLE, 
TAPERED, 450 SWEPTBACK, ASPECT-RATIO-4 
TAIL DEFLECTED ABOUT A SKEWED HINGE AXIS 
AND EQUIPPED WITH AN INSET UNBALANCING 
TAB. James M. Watson. September 1953. 40p. 
diagrs. (NACA RM L53H13) 



AUTOMATIC CONTROL 
(1.8.2.6) 



THEORETICAL ANALYSIS OF THE ROLLING 
MOTIONS OF AIRCRAFT USING A FLICKER-TYPE 
AUTOMATIC ROLL STABILIZATION SYSTEM 
HAVING A DISPLACEMENT-PLUS-RATE 
RESPONSE. Howard J. Curfman, Jr. January 12, 
1949. 29p. diagrs., 2 tabs. (NACA RM L8K23a) 

AN EXPERIMENTAL INVESTIGATION OF A GYRO- 
ACTUATED ROLL CONTROL SYSTEM INSTALLED 
IN A SUBSONIC TEST VEHICLE. Jerome M. 
Teitelbaum and Ernest C. Seaberg. April 20, 1949. 
26p. diagrs., photos., tab. (NACA RM L9B24a) 

LABORATORY INVESTIGATION OF AN AUTOPILOT 
UTILIZING A MECHANICAL LINKAGE WITH A DEAD 
SPOT TO OBTAIN AN EFFECTIVE RATE SIGNAL. 
Ernest C. Seaberg. August 17, 1949. 29p. diagrs., 
photos., tab. (NACA RM L9F15a) 

A THEORETICAL INVESTIGATION OF THE INFLU- 
ENCE OF AUXILIARY DAMPING IN PITCH ON THE 
DYNAMIC CHARACTERISTICS OF A PROPORTION- 
ALLY CONTROLLED SUPERSONIC CANARD MIS- 
SILE CONFIGURATION. Walter C. Nelson and 
Anthony L. Passera. August 25, 1950. 46p. 
diagrs., photo., 3 tabs. (NACA RM L50F30) 



THEORETICAL INVESTIGATION OF AN AUTO- 
MATIC CONTROL SYSTEM WITH PRIMARY SENSI- 
TIVITY TO NORMAL ACCELERATIONS AS USED 
TO CONTROL A SUPERSONIC CANARD MISSILE 
CONFIGURATION. Ernest C. Seaberg and Earl F. 
Smith. July 1951. 48p. diagrs., photo., 3 tabs. 
(NACA RM L51D23) 



SYSTEM ANALYSES AND AUTOPILOT DESIGN FOR 
AUTOMATIC ROLL STABIUZATION OF A SUPER- 
SONIC PILOTLESS AIRCRAFT. Jacob Zarovsky. 
July 1951. 55p. diagrs., tab. (NACA RM L51E07) 

A THEORETICAL INVESTIGATION OF THE INFLU- 
ENCE OF AUTOPILOT NATURAL FREQUENCY 
UPON THE DYNAMIC PERFORMANCE CHARAC- 
TERISTICS OF A SUPERSONIC CANARD MISSILE 
CONFIGURATION WITH A PITCH -ATTITUDE CON- 
TROL SYSTEM. Anthony L. Passera. October 

1951. 32p. diagrs., photos., 2 tabs. (NACA 
RM L51H02) 

A THEORETICAL INVESTIGATION OF THE 
EFFECT OF A TARGET SEEKER SENSITIVE TO 
PITCH ATTITUDE ON THE DYNAMIC STABILITY 
AND RESPONSE CHARACTERISTICS OF A SUPER- 
SONIC CANARD MISSILE CONFIGURATION. 
Ordway B. Gates, Jr. and Albert A. Schy. August 

1952. 54p. diagrs., photo., tab. (NACA 
RM L52E19) 

THE EFFECT OF CONTROL-SURFACE-SERVO 
NATURAL FREQUENCY ON THE DYNAMIC PER- 
FORMANCE CHARACTERISTICS OF AN ACCELER- 
ATION CONTROL SYSTEM APPLIED TO A SUPER- 
SONIC MISSILE. Anthony L. Passera and Martin L. 
Nason. September 1953. 28p. diagrs., 3 tabs. 
(NACA RM L53G23a) 

THEORETICAL INVESTIGATION OF LONGITUDINAL 
RESPONSE CHARACTERISTICS OF A SWEPT-WING 
FIGHTER AIRPLANE HAVING A NORMAL- 
ACCELERATION CONTROL SYSTEM AND A COM- 
PARISON WITH OTHER TYPES OF SYSTEMS. Fred 
H. Stokes and Charles W. Mathews. July 1954. 50p. 
diagrs., tab. (NACA TN 3191) 

THEORETICAL ANALYSIS OF AN AIRPLANE 
ACCELERATION RESTRICTOR CONTROLLED BY 
NORMAL ACCELERATION, PITCHING ACCELERA- 
TION, AND PITCHING VELOCITY. Christopher C. 
Kraft, Jr. September 1954. 42p. diagrs., 3 tabs. 
(NACA TN 3243) 

OPERATING CHARACTERISTICS OF AN 
ACCELERATION RESTRICTOR AS DETERMINED 
BY MEANS OF A SIMULATOR. Arthur 
Assadourian. December 1954. 20p. dlagrs., 
photos. (NACA TN 3319) 



USE OF NONLINEARITIES TO COMPENSATE FOR 
THE EFFECTS OF A RATE -LIMITED SERVO ON 
THE RESPONSE OF AN AUTOMATICALLY CON- 
TROLLED AIRCRAFT. Stanley F. Schmidt and 
William C. Triplett. January 1955. 27p. diagrs., 
tab. (NACA TN 3387) 



FLIGHT TESTING BY RADIO REMOTE CONTROL - 
FLIGHT EVALUATION OF A BEEP-CONTROL 
SYSTEM. Howard L. Turner, John S. White and 
Rudolph D. Van Dyke, Jr. March 1955. 55p. 
diagrs., photos., tab. (NACA TN 3496. Formerly 
RM A52A29) 

THEORETICAL INVESTIGATION OF A 
PROPORTIONAL-PLUS-FLICKER AUTOMATIC 
PILOT. Ernest C. Seaberg. May 1955. 53p. 
diagrs., photo., tab. (NACA TN 3427. Formerly 
RM L50I19) 



104 



AERODYNAMICS 
STABILITY AND CONTROL (1.8) 



SPINNING 
(1.8,3) 



AN INVESTIGATION OF THE SPIN, RECOVERY, 
AND TUMBLING CHARACTERISTICS OF A 1/20- 
SCALE MODEL OF THE NORTHROP X-4 AIRPLANE. 
Lawrence J. Gale, Ira P. Jones, Jr. and Jack H. 
Wilson. January 4, 1950. 27p. diagrs., photos., 4 
tabs. (NACA RM L9K28) 

SPIN-TUNNEL INVESTIGATION OF A MODEL OF 
A 60° DELTA-WING AIRPLANE TO DETERMINE 
THE SPIN, RECOVERY, AND LONGITUDINAL 
TRIM CHARACTERISTICS THROUGHOUT AN 
EXTENSIVE RANGE OF MASS LOADINGS. Walter 
J. KUnar and Ira P. Jones, Jr. February 15, 1950. 
56p. diagrs. , photos. , 6 charts, 4 tabs. 
(NACA RM L9L06) 

SPIN AND RECOVERY CHARACTERISTICS OF A 
MODEL OF A FIGHTER TYPE OF AIRPLANE WITH- 
OUT A HORIZONTAL TAIL AND HAVING EITHER A 
SINGLE VERTICAL TAIL OR TWIN VERTICAL 
TAILS. Lawrence J. Gale and Norn-.an E. 
Pumphrey. July 25, 1950. 23p. diagrs., photos., 
2 tabs. (NACA RM L50F19a) 

SPIN-TUNNEL INVESTIGATION OF A MODEL OF 
A SWEPT-WING FIGHTER AIRPLANE OVER A 
WIDE RANGE OF FUSELAGE -HEAVY LOADINGS. 
Theodore Berman. December 27, 1950. 51p. 
diagrs., photos., 2 tabs. (NACA RM L50L08) 

STATIC LONGITUDINAL STABILITY AND 
DYNAMIC CHARACTERISTICS AT HIGH ANGLES 
OF ATTACK AND AT LOW REYNOLDS NUMBERS 
OF A MODEL OF THE X-3 SUPERSONIC RESEARCH 
AIRPLANE. Sanger M. Burk, Jr. and Burton E. 
Hultz. February 6, 1951. 76p. diagrs., photos., 
4 tabs. (NACA RM L50L19) 

EFFECT OF CURRENT DESIGN TRENDS ON AIR- 
PLANE SPINS AND RECOVERIES. Anshal I. 
Neihouse. January 1952. 6p. diagrs. (NACA RM 
L52A09) 



AN ANALYTICAL INVESTIGATION OF AIRPLANE 
SPIN-RECOVERY MOTION BY USE OF ROTARY- 
BALANCE AERODYNAMIC DATA. Stanley H. Scher. 
June 1954. 38p. diagrs., tab. (NACA TN 3188) 

ANALYTICAL DETERMINATION OF THE 
MECHANISM OF AN AIRPLANE SPIN RECOVERY 
WITH DIFFERENT APPLIED YAWING MOMENTS 
BY USE OF ROTARY-BALANCE DATA. Sanger M. 
Burk, Jr. December 1954. 43p. diagrs., 2 tabs. 
(NACA TN 3321) 



STALLING 
(1.8.4) 



DRAG MEASUREMENTS OF A SWEPT -BACK WING 
HAVING INVERSE TAPER AS DETERMINED BY 
FLIGHT TESTS AT SUPERSONIC SPEEDS. Sidney 
R. Alexander. April 8, 1947. 12p. diagrs., photo. 
(NACA RM L6L30) 



MEASUREMENTS OF THE WING AND TAIL LOADS 
DURING THE ACCEPTANCE TESTS OF BELL XS-1 
RESEARCH AIRPLANE. De E. Beeler and John P. 
Mayer. April 13, 1948. 25p. diagrs., photos., 2 
tabs. (NACA RM L7L12) 

GENERAL HANDLING-QUALITIES RESULTS 
OBTAINED DURING ACCEPTANCE FLIGHT TESTS 
OF THE BELL XS-1 AIRPLANE. Walter C. 
Williams, Charles M. Forsyth and Beverly P. 
Brown. April 19, 1948. 72p. diagrs., photos., tab. 
(NACA RM L8A09) 

LANDING CHARACTERISTICS OF HIGH-SPEED 
WINGS. Herbert A. Wilson, Jr. and Laurence K. 
Loftin, Jr. September 21, 1948. 21p. diagrs. 
(NACA RM L8A28e) 

MAXfiVIUM-LIFT INViBTIGATION AT MACH NUM- 
BERS FROM 0.05 TO 1.20 OF A WING WITH LEAD- 
ING EDGE SWEPT BACK 42°. Thomas R. Turner. 
February 14, 1950. 21p. diagrs. (NACA 
RM L9K03) 

STALL CHARACTERISTICS OBTAINED FROM 
FLIGHT 10 OF NORTHROP X-4 NO. 2 AIRPLANE 
(USAF NO. 46-677). Melvin Sadoff and Thomas R. 
Sisk. February 27, 1950. 25p. diagrs., photos., tab. 
(NACA RM A50A04) 

MAXIMUM-LIFT INVESTIGATION OF A 1/40-SCALE 
X-1 AIRPLANE WING AT MACH NUMBERS FROM 
0.60 TO 1.15. Thomas R. Turner. J^rll 21, 1950. 
18p. diagrs. (NACA RM L50C28) 

EFFECTS OF SWEEP ON THE MAXIMUM-LIFT 
CHARACTERISTICS OF FOUR ASPECT -RATIO-4 
WINGS AT TRANSONIC SPEEDS. Thomas R. Turner. 
October 3, 1950. 25p. diagrs. (NACA RM L50H11) 



SUMMARY REPORT OF RESULTS OBTAINED DUR- 
ING DEMONSTRATION TESTS OF THE NORTHROP 
X-4 AIRPLANES. Melvin Sadoff and Thomas R. 
Sisk. December 13, 1950. 46p. diagrs., photos., 
tab. (NACA RM A50I01) 

EFFECT OF A DEFLECTABLE WING-TIP CON- 
TROL ON THE LOW-SPEED LATERAL AND 
LONGITUDINAL CHARACTERISTICS OF A LARGE- 
SCALE WING WITH THE LEADING EDGE SWEPT 
BACK 47.5°. Roy H. Lange and Marvin P. Fink. 
April 26, 1951. 41p. diagrs., photo., 2 tabs. 
(NACA RM L51C07) 

FLIGHT DETERMINATION OF THE EFFECTS OF 
WING VORTEX GENERATORS ON THE AERO- 
DYNAMIC CHARACTERISTICS OF THE DOUGLAS 
D-558-I AIRPLANE. De E. Beeler, Donald R. 
Bellman and John H. Griffith. August 14, 1951. 23p. 
diagrs., photos., tab. (NACA RM L51A23) 

STABILITY AND CONTROL MEASUREMENTS OB- 
TAINED DURING USAF -NACA COOPERATIVE 
FLIGHT-TEST PROGRAM ON THE X-4 AIRPLANE 
(USAF NO. 46-677). Melvin Sadoff, Herman O. 
Ankenbruck and William O'Hare. October 1951. 38p. 
diagrs., photos., tab. (NACA RM A51H09) 

FULL-SCALE WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF WING MODIFICATIONS AND 
HORIZONTAL-TAIL LOCATION ON THE LOW- 
SPEED STATIC LONGITUDINAL CHARACTERISTICS 
OF A 35° SWEPT-WING AIRPLANE. Ralph L. Maki. 
April 1952. 54p. diagrs., photos., 7 tabs. (NACA 
RM A52B05) 



AERODYNAMICS 

STABILITY AND CONTROL (1.8) 



105 



Stalling (Cont. ) 

PRELDUDJARY STtJDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTERIS- 
TICS OF THBSt WINGS. A. Gerald Rainey. July 1952. 
33p. diagrs., photo., tab. (NACA RM L52D08) 

SOME OBSERVATIONS ON STALL FLUTTER AND 
BUFFETING. A. Gerald Rainey. June 1953. lip. 
diagrs. (NACA RM L53E15) 

METHOD FOR CALCULATING THE ROLLING AND 
YAWING MOMENTS DUE TO ROLLING FOR UN- 
SWEPT WINGS WITH OR WITHOUT FLAPS OR 
AILERONS BY USE OF NONLINEAR SECTION LIFT 
DATA. Albert P. Martina. 1954. ii, 16p. diagrs., 
11 tabs. (NACA Rept. 1167. Formerly TN 2937) 

PRELIMINARY INVESTIGATION OF A STICK 
SHAKER AS A LIFT -MARGIN INDICATOR. James 
P. Trant, Jr. February 1955. 19p. diagrs., 
photos. (NACA TN 3355) 



FLYING QUALITIES 

(i.s.s) 



GENERAL HANDLING-QUALITIES RESULTS 
OBTAINED DURING ACCEPTANCE FLIGHT TESTS 
OF THE BELL XS-1 AIRPLANE. Walter C. 
Williams, Charles M. Forsyth and Beverly P. 
Brown. April 19, 1948. 72p. diagrs., photos., tab. 
(NACA RM L8A09) 



FACTORS AFFECTING LATERAL STABILITY AND 
CONTROLLABILITY. John P. Campbell and 
Thomas A. Toll. May 13, 1948. 19p. diagrs. 
(NACA RM L8A28a) 



THEORETICAL INVESTIGATION OF THE DYNAMIC 
LATERAL STABILITY CHARACTERISTICS OF 
DOUGLAS DESIGN NO. 39C, AN EARLY VERSION 
OF THE X-3 RESEARCH AIRPLANE. Charles V. 
Bennett. January 18, 1949. 39p. diagrs., 2 tabs. 
(NACA RM L8L31) 



STABILITY AND CONTROL DATA OBTAINED FROM 
FIRST FUGHT OF X-4 AIRPLANE. Hubert M. 
Drake. February 7, 1949. lip. diagrs., photos., 
tab. (NACA RM L9A31) 

STABILITY RESULTS OBTAINED WITH DOUGLAS 
D-558-1 AIRPLANE (BUAERO NO. 37971) IN 
FLIGHT UP TO A MACH NUMBER OF 0.89. 
WUliam H. Barlow and Howard C. LUly. April 22, 
1949. 16p. diagrs., photos. (NACA RM L8K03) 



MEASUREMENT OF THE DYNAMIC LATERAL 
STABILITY OF THE DOUGLAS D-558-1 AIRPLANE 
(BUAERO NO. 37971) IN RUDDER KICIffi AT A MACH 
NUMBER OF 0.72. Hubert M. Drake. May 31, 1949. 
lOp. diagrs., photos. (NACA RM L9D06a) 



RESULTS OBTAINED FROM SECOND FLIGHT OF 
X-4 AIRPLANE (A.F. NO. 46-676). Walter C. 
Williams. July 18, 1949. 13p. diagrs., photos., tab. 
(NACA RM L9F21) 



STABILITY AND CONTROL DATA OBTAINED FROM 
FOURTH AND FIFTH FLIGHTS OF THE NORTHROP 
X-4 AIRPLANE (A.F. NO. 46-676). George M. 
Valentine. August 4, 1949. 22p. diagrs., photos., 
tab. (NACA RM L9G25a) 

RESULTS OBTAINED FROM THIRD FUGHT OF 
NORTHROP X-4 AIRPLANE (A.F. NO. 46-676). 
Walter C. Williams. September 9, 1949. 13p. 
diagrs., photos., tab. (NACA RM L9G20a) 



A STUDY OF THE DYNAMIC STABILITy OF THE 
BELL X-1 RESEARCH AIRPLANE. Edward C. 
Polhamus. January 10, 1950. 16p. diagrs., tab. 
(NACA RM L9K04a) 



RESULTS OBTAINED DURING FLIGHTS 1 TO 6 OF 
THE NORTHROP X-4 AIRPLANE (A.F. NO. 46-677). 
James T. Matthews, Jr. January 12, 1950. 19p. 
diagrs., photos., tab. (NACA RM L9K22) 



STALL CHARACTERISTICS OBTAINED FROM 
FLIGHT 10 OF NORTHROP X-4 NO. 2 AIRPLANE 
(USAF NO. 46-677). Melvin SadoH and Thomas R. 
Sisk. February 27, 1950. 25p. diagrs., photos., tab. 
(NACA RM A50A04) 



THEORETICAL INVESTIGATION OF THE DYNAMIC 
LATERAL STABILITY CHARACTERISTICS OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE, STUDY 
41 -B. Charles V. Bennett. April 27, 1950. 31p. 
diagrs., 3 tabs. (NACA RM L50B28) 



FLIGHT INVESTIGATION OF THE AILERON CHAR- 
ACTERISTICS OF THE DOUGLAS D-558-1 AIR- 
PLANE (BUAERO NO. 37972) AT MACH NUMBERS 
BETWEEN 0.6 AND 0.89. Jim Rogers Thompson, 
William S. Roden and John M. Eggleston. May 26. 
1950. 23p. diagrs., photos., tab. (NACA 
RM L50D20) 



LONGITUDINAL-STABILITY CHARACTERISTICS OF 
THE NORTHROP X-4 AIRPLANE (USAF NO. 46-677). 
Melvin Sadoff and Thomas R. Sisk. June 29, 1950. 
24p. diagrs., photos., tab. (NACA RM A50D27) 

EFFECTS ON THE LATERAL OSCILLATION OF 
FIXING THE RUDDER AND REFLEXING THE 
FLAPS ON THE BELL X-1 AIRPLANE. Hubert M. 
Drake. December 11, 1950. 14p. diagrs., photo. 
(NACA RM L50I05) 



SUMMARY REPORT OF RESULTS OBTAINED DUR- 
ING DEMONSTRATION TESTS OF THE NORTHROP 
X-4 AIRPLANES. Melvin Sadoff and Thomas R. 
Sisk. December 13, 1950. 46p. diagrs., photos., 
tab. (NACA RM A50I01) 

EFFECTS ON THE SNAKING OSCILLATION OF THE 
BELL X-1 AIRPLANE OF A TRAILING-EDGE BULB 
ON THE RUDDER. Hubert M. Drake and Harry P. 
Clagett. January 16, 1951. 14p. diagrs., photo. 
(NACA RM L50K01a) 

FLIGHT INVESTIGATION OF THE LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
THE DOUGLAS D-558-1 AIRPLANE (BUAERO 
NO 37972) AT MACH NUMBERS UP TO 0.89. Melvin 
Sadoff, William S. Roden and John M. Eggleston. 
June 1951. 26p. diagrs., photos., tab. (NACA 
RM L51D18) 



AERODYNAMICS 
106 STABILITY AND CONTROL (1.8) 



Flying Qualities (Cont. ) 



A COMPARISON OF THE MEASURED AND PRE- 
DICTED LATERAL OSCILLATORY CHARACTER- 
ISTICS OF A 350 SWEPT -WING FIGHTER AIR- 
PLANE. Walter E. McNeill and George E. Cooper. 
July 1951. 21p. diagrs., 3 tabs. (NACARMA51C28) 

A FLIGHT STUDY OF REQUIREMENTS FOR SATIS- 
FACTORY LATERAL OSCILLATORY CHARACTER- 
ISTICS OF FIGHTER AIRCRAFT. Charles J. 
Liddell, Jr., Brent Y. Creer and Rudolph D. 
Van Dyke, Jr. July 1951. 39p. diagrs., photo., 
2 tabs. (NACA RM A51E16) 

STABILITY AND CONTROL MEASUREMENTS OB- 
TAINED DURING USAF-NACA COOPERATIVE 
FLIGHT-TEST PROGRAM ON THE X-4 AIRPLANE 
(USAF NO. 46-677). Melvln Sadott, Herman O. 
Ankenbruck and William O'Hare. October 1951. 38p. 
diagrs., photos., tab. (NACA RM A51H09) 

SOME FLYING-QUALITIES STUDIES OF A TANDEM 
HELICOPTER. Kenneth B. Amer. October 1951. 
29p. diagrs., photos. (NACA RM L51H20aj 

LOW-SPEED TESTS OF A FREE-TO-YAW MODEL 
IN TWO WIND TUNNELS OF DIFFERENT TURBU- 
LENCE. Jones F. Cahill and John D. Bird. 
February 1952. 12p. diagrs., photos. (NACA 
RM L51L14) 

FLIGHT MEASUREMENTS OF THE LATERAL STA- 
BILITY AND CONTROL CHARACTERISTICS OF A 
HIGH-SPEED FIGHTER AIRPLANE. H. L. Crane, 

A. R, Beckhardt and C. E. Matheny. September 
1952. 50p. diagrs., tab. (NACA RM L52B14) 

TESTS OF A CENTERING SPRING USED AS AN AR- 
TIFICAL FEEL DEVICE ON THE ELEVATOR OF A 
FIGHTER AIRPLANE. James J. Adams and James 

B. Whitten. September 1952. 18p. diagrs., photo, 
tab. (NACA RM L52G16) 

THE EFFECTS ON DYNAMIC LATERAL STABILITY 
AND CONTROL OF LARGE ARTIFICIAL VARIA- 
TIONS IN THE ROTARY STABIUTY DERIVATIVES. 
Robert O. Schade and James L. Hassell, Jr. 1953. 
ii, 24p. diagrs., photo., 2 tabs. (NACA Rept. 1151. 
Formerly TN 2781) 

FLIGHT TESTS OF A MAN STANDING ON A PLAT- 
FORM SUPPORTED BY A TEETERING ROTOR. 
Paul R. HUl and T. L. Kennedy. March 1954. 26p. 
diagrs., photos. (NACA RM L54B12a) 

DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A CASCADE-WING VERTICALLY RISING 
AIRPLANE MODEL IN TAKE-OFFS, LANDINCK, 
AND HOVERING FLIGHT. Marion O. McKinney, 
Louis P. Tosti and Edwin E. Davenport. June 1954. 
45p. diagrs., photos., tab. (NACA TN 3198) 

ANALYTICAL DETERMINATION OF THE 
MECHANISM OF AN AIRPLANE SPIN RECOVERY 
WITH DIFFERENT APPLIED YAWING MOMENTS 
BY USE OF ROTARY-BALANCE DATA. Sanger M. 
Burk, Jr. December 1954. 43p. diagrs., 2 tabs. 
(NACA TN 3321) 

FLIGHT TESTING BY RADIO REMOTE CONTROL - 
FLIGHT EVALUATION OF A BEEP-CONTROL 
SYSTEM. Howard L. Turner, John S. White and 
Rudolph D. Van Dyke, Jr. March 1955. 55p. 
diagrs., photos., tab. (NACA TN 3496. Formerly 
RM A52A29) 



SOME CALCULATIONS OF THE LATERAL RE- 
SPONSE OF TWO AIRPLANES TO ATMOSPHERIC 
TURBULENCE WITH RELATION TO THE LATERAL 
SNAKING PROBLEM. John D. Bird. May 1955. 
24p. diagrs., 2 tabs. (NACA TN 3425. Formerly 
RM L50F26a) 

HOVERING FLIGHT TESTS OF A FOUR-ENGINE- 
TRANSPORT VERTICAL TAKE-OFF AIRPLANE 
MODEL UTILIZING A LARGE FLAP AND EXTEN- 
SIBLE VANES FOR REDIRECTING THE PROPEL- 
LER SLIPSTREAM. Louis P. Tosti and Edwin E. 
Davenport. May 1955. 26p. diagrs., photos., tab. 
(NACA TN 3440) 



MASS AND 
GYROSCOPIC PROBLEMS 

(1.8.6) 

SUMMARY OF RESULTS OF TUMBUNG INVESTI- 
GATIONS MADE IN THE LANGLEY 20-FOOT FREE- 
SPINNING TUNNEL ON 14 DYNAMIC MODELS. 
Ralph W. Stone, Jr. and Robert L. Bryant. 
December 31, 1948. 91p. diagrs., photos., 23 tabs. 
(NACA RM L8J28) 

AN EMPIRICAL CRITERION FOR FIN STABI- 
LIZING JETTISONABLE NOSE SECTIONS OF AIR- 
PLANES. Stanley H. Scher. December 8, 1949. 
21p. diagrs., photo., tab. (NACA RM L9I28) 



AN INVESTIGATION OF THE SPIN, RECOVERY, 
AND TUMBUNG CHARACTERISTICS OF A 1/20- 
SCALE MODEL OF THE NORTHROP X-4 AIRPLANE. 
Lawrence J. Gale, Ira P. Jones, Jr. and Jack H. 
Wilson. January 4, 1950. 27p. diagrs., photos., 4 
tabs. (NACA RM L9K28) 

SPIN-TUNNEL INVESTIGATION OF A MODEL OF 
A 60° DELTA-WING AIRPLANE TO DETERMINE 
THE SPIN, RECOVERY, AND LONGITUDINAL 
TRIM CHARACTERISTICS THROUGHOUT AN 
EXTENSIVE RANGE OF MASS LOADINGS. Walter 
J. Kllnar and Ira P. Jones, Jr. February 15, 1950. 
56p. diagrs. , photos. , 6 charts, 4 tabs. 
(NACA RM L9L06) 

SPIN AND RECOVERY CHARACTERISTICS OF A 
MODEL OF A FIGHTER TYPE OF AIRPLANE WITH- 
OUT A HORIZONTAL TAIL AND HAVING EITHER A 
SINGLE VERTICAL TAIL OR TWIN VERTICAL 
TAILS. Lawrence J. Gale and Nornr.an E. 
Pumphrey. July 25, 1950. 23p. diagrs., photos., 
2 tabs. (NACA RM L50F19a) 

PRELIMINARY EMPIRICAL DESIGN REQUIRE- 
MENTS FOR THE PREVENTION OF TUMBLING OF 
AIRPLANES HAVING NO HORIZONTAL TAILS. 
Robert L. Bryant. October 11, 1950. 23p. diagrs., 
2 tabs. (NACA RM L50H23) 

EFFECTS ON THE LATERAL OSCILLATION OF 
FIXING THE RUDDER AND REFLEXING THE 
FLAPS ON THE BELL X-1 AIRPLANE. Hubert M. 
Drake. December 11, 1950. 14p. diagrs., photo. 
(NACA RM L50I05) 

SPIN-TUNNEL INVESTIGATION OF A MODEL OF 
A SWEPT -WING FIGHTER AIRPLANE OVER A 
WIDE RANGE OF FUSELAGE-HEAVY LOADINGS. 
Theodore Herman. December 27, 1950. 51p. 
diagrs., photos., 2 tabs. (NACA RM L50L08) 



AERODYNAMICS 

STABILITY AND CONTROL (1.8) 



107 



Mass and Gyroscopic Problems 
(Cont. ) 

STATIC LONGITUDINAL STABILITY AND 
DYNAMIC CHARACTERISTICS AT HIGH ANGLES 
OF ATTACK AND AT LOW REYNOLDS NUMBERS 
OF A MODEL OF THE X-3 SUPERSONIC RESEARCH 
AIRPLANE. Sanger M. Burk, Jr. and Burton E. 
Hultz. February 6, 1951. 76p. diagrs., photos., 
4 tabs. (NACA RM L50L19) 

THE EFFECT OF MASS DISTRIBUTION ON THE 
LOW-SPEED DYNAMIC LATERAL STABILITY AND 
CONTROL CHARACTERISTICS OF A MODEL WITH 
A 60° TRIANGULAR WING. Joseph L. Johnson. 
March 9, 1951. 23p. diagrs., 2 tabs. (NACA 
RM L50K10) 

EFFECT OF CURRENT DESIGN TRENDS ON AIR- 
PLANE SPINS AND RECOVERIES. Anshal I. 
Neihouse. January 1952. 6p. diagrs. (NACA RM 
L52A09) 

ANALYTICAL DETERMINATION OF THE 
MECHANISM OF AN AIRPLANE SPIN RECOVERY 
WITH DIFFERENT APPLIED YAWING MOMENTS 
BY USE OF ROTARY-BALANCE DATA. Sanger M. 
Burk, Jr. December 1954. 43p. diagrs., 2 tabs. 
(NACA TN 3321) 

EFFECTIVE MOMENT OF INERTIA OF FLUID IN 
OFFSET, INCLINED, AND SWEPT -WING TANKS 
UNDERGOING PITCHING OSCILLATIONS. James 
R. Reese and John L. Sewall. January 1955. 27p. 
diagrs., 6 tabs. (NACA TN 3353) 



TUMBLING 
(1.8.7) 



SUMMARY OF RESULTS OF TUMBLING INVESTI- 
GATIONS MADE IN THE LANGLEY 20-FOOT FREE- 
SPINNING TUNNEL ON 14 DYNAMIC MODELS. 
Ralph W. Stone, Jr. and Robert L. Bryant. 
December 31, 1948. 91p. diagrs., photos., 23 tabs. 
(NACA RM L8J28) 

AN INVESTIGATION OF THE SPIN, RECOVERY, 
AND TUMBLING CHARACTERISTICS OF A 1/20- 
SCALE MODEL OF THE NORTHROP X-4 AIRPLANE. 
Lawrence J. Gale, Ira P. Jones, Jr. and Jack H. 
Wilson. January 4, 1950. 27p. diagrs., photos., 4 
tabs. (NACA RM L9K28) 

PRELIMINARY EMPIRICAL DESIGN REQUIRE- 
MENTS FOR THE PREVENTION OF TUMBLING OF 
AIRPLANES HAVING NO HORIZONTAL TAILS. 
Robert L. Bryant. October 11, 1950. 23p. 
2 tabs. (NACA RM L50H23) 



AUTOMATIC STABILIZATION 
(l.B.s) 



A THEORETICAL INVESTIGATION OF THE INFLU- 
ENCE OF AUXILIARY DAMPING IN PITCH ON THE 
DYNAMIC CHARACTERISTICS OF A PROPORTION- 
ALLY CONTROLLED SUPERSONIC CANARD MIS- 
SILE CONFIGURATION. Walter C. Nelson and 
Anthony L. Passera. August 25, 1950. 46p. 
diagrs., photo., 3 tabs. (NACA RM L50F30) 



THEORETICAL INVESTIGATION OF AN AUTO- 
MATIC CONTROL SYSTEM WITH PRIMARY SENSI- 
TIVITY TO NORMAL ACCELERATIONS AS USED 
TO CONTROL A SUPERSONIC CANARD MISSILE 
CONFIGURATION. Ernest C. Seaberg and Earl F. 
Smith. July 1951. 48p. diagrs., photo., 3 tabs. 
(NACA RM L51D23) 

SYSTEM ANALYSES AND AUTOPILOT DESIGN FOR 
AUTOMATIC ROLL STABILIZATION OF A SUPER- 
SONIC PILOTLESS AIRCRAFT. Jacob Zarovsky. 
July 1951. 55p. diagrs., tab. (NACA RM L51E07) 

A THEORETICAL INVESTIGATION OF THE INFLU- 
ENCE OF AUTOPILOT NATURAL FREQUENCY 
UPON THE DYNAMIC PERFORMANCE CHARAC- 
TERISTICS OF A SUPERSONIC CANARD MISSILE 
CONFIGURATION WITH A PITCH -ATTITUDE CON- 
TROL SYSTEM. Anthony L. Passera. October 

1951. 32p. diagrs., photos., 2 tabs. (NACA 
RM L51H02) 

A THEORETICAL INVESTIGATION OF THE 
EFFECT OF A TARGET SEEKER SENSITIVE TO 
PITCH ATTITUDE ON THE DYNAMIC STABILITY 
AND RESPONSE CHARACTERISTICS OF A SUPER- 
SONIC CANARD MISSILE CONFIGURATION. 
Ordway B. Gates, Jr. and Albert A. Schy. August 

1952. 54p. diagrs., photo., tab. (NACA 
RM L52E19) 

THE EFFECTS ON DYNAMIC LATERAL STABILITY 
AND CONTROL OF LARGE ARTIFICIAL VARIA- 
TIONS IN THE ROTARY STABIUTY DERIVATIVES. 
Robert O. Schade and James L. Hassell, Jr. 1953. 
ii, 24p. diagrs., photo., 2 tabs. (NACA Rept. 1151. 
Formerly TN 2781) 

THE EFFECT OF CONTROL-SURFACE -SERVO 
NATURAL FREQUENCY ON THE DYNAMIC PER- 
FORMANCE CHARACTERISTICS OF AN ACCELER- 
ATION CONTROL SYSTEM APPLIED TO A SUPER- 
SONIC MISSILE. Anthony L. Passera and Martin L. 
Nason. September 1953. 28p. diagrs., 3 tabs. 
fNACA RM L53G23a) 

DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A CASCADE-WING VERTICALLY RISING 
AIRPLANE MODEL IN TAKE-OFFS, LANDINGS, 
AND HOVERING FLIGHT. Marion O. McKinney, 
Louis P. Tosti and Edwin E. Davenport. June 1954. 
45p. diagrs., photos., tab. (NACA TN 3198) 

THEORETICAL INVESTIGATION OF LONGITUDINAL 
RESPONSE CHARACTERISTICS OF A SWEPT-WING 
FIGHTER AIRPLANE HAVING A NORMAL- 
ACCELERATION CONTROL SYSTEM AND A COM- 
PARISON WITH OTHER TYPES OF SYSTEMS. Fred 
H. Stokes and Charles W. Mathews. July 1954. 50p. 
diagrs., tab. (NACA TN 3191) 

USE OF NONLINEARITIES TO COMPENSATE FOR 
THE EFFECTS OF A RATE -LIMITED SERVO ON 
THE RESPONSE OF AN AUTOMATICALLY CON- 
TROLLED AIRCRAFT. Stanley F. Schmidt and 
William C. Triplett. January 1955. 27p. diagrs., 
tab. (NACA TN 3387) 

THEORETICAL INVESTIGATION OF A 
PROPORTIONAL-PLUS-FLICKER AUTOMATIC 
PILOT. Ernest C. Seaberg. May 1955. 53p. 
diagrs., photo., tab. (NACA TN 3427. Formerly 
RM L50I19) 

HOVERING FLIGHT TESTS OF A FOUR-ENGINE- 
TRANSPORT VERTICAL TAKE-OFF AIRPLANE 
MODEL UTILIZING A LARGE FLAP AND EXTEN- 
SIBLE VANES FOR REDIRECTING THE PROPEL- 
LER SLIPSTREAM. Louis P. Tosti and Edwin E. 
Davenport. May 1955. 26p. diagrs., photos., tab. 
(NACA TN 3440) 



108 AERODYNAMICS 



Aeroelasticity 
(1.9) 



A TORSIONAL STIFFNESS CRITERION FOR PRE- 
VENTING FLUTTER OF WINGS OF SUPERSONIC 
MISSILES. Bernard Budiansky, Joseph N. Kotanchifc 
and Patrick T. Chiarito. August 28, 1947. 14p. 
diagrs., tab. (NACA RM L7G02) 

EFFECTS OF MACH NUMBER AND SWEEP ON THE 
DAMPDJG-IN-ROLL CHARACTERISTICS OF WINGS 
OF ASPECT RATIO 4. Richard E. Kuhn and Boyd 
C. Myers, II. June 27, 1949. 28p. diagrs. photo. 
(NACA RM L9E10) 

WING-FLOW MEASUREMENTS OF LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
A CANARD AIRPLANE CONFIGURATION WITH A 
45° SWEPTBACK WING AND A TRIANGULAR ALL- 
MOVABLE CONTROL SURFACE. Harold L. Crane 
and James J. Adams. August 25, 1950. 53p. 
diagrs., photo. (NACA RM L50A31) 

AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBER OF 1.38 OF FOUR WiNGS OF ASPECT 
RATIO 4 HAVING QUARTER-CHORD SWEEP 
ANGLES OF 0°, 35°, 450, AND 60O. William B. 
Kemp, Jr., Kenneth W. Goodson and Robert A. Booth. 
October 10, 1950. 41p. diagrs., photos., tab. 
(NACA RM L50G14) 

DESCRIPTION AND INVESTIGATION OF A 
DYNAMIC MODEL OF THE XH-17 TWO-BLADE 
JET -DRIVEN HELICOPTER. George W. Brooks and 
Maurice A. Sylvester. March 14, 1951. 49p. 
diagrs., photos., 6 tabs. (NACA RM L50I21) 

FLUTTER INVESTIGATION OF TWO THIN, LOW- 
ASPECT-RATIO, SWEPT, SOLID, METAL WINGS 
IN THE TRANSONIC RANGE BY USE OF A FREE- 
FALLINGBODY. W. T. Lauten, Jr. and Maurice 
A. Sylvester. February 1952. 12p. diagrs., photo., 
2 tabs. (NACA RM L51K28a) 

THE CALCULATION OF CERTAIN STATIC AERO- 
ELASTIC PHENOMENA OF WINGS WITH TIP 
TANKS OR BOOM-MOUNTED LIFTING SURFACES. 
Franklin W. Diederich and Kenneth A. Foss. 
August 1952. 55p. diagrs., 2 tabs. (NACA 
RM L52A22) 

FLIGHT MEASUREMENTS OF THE LATERAL STA- 
BILITY AND CONTROL CHARACTERISTICS OF A 
HIGH-SPEED FIGHTER AIRPLANE. H. L. Crane, 
A. R. Beckhardt and C. E. Matheny. September 
1952. 50p. diagrs., tab. 



LATERAL AND DIRECTIONAL DYNAMIC - 
RESPONSE CHARACTERISTICS OF A 35° SWEPT- 
WING AIRPLANE AS DETERMINED FROM FLIGHT 
MEASUREMENTS. William C. Triplett and 
Stuart C. Brown. December 1952. 62p. diagrs., 
photo., 3 tabs. (NACA RM A52I17) 



LIFT AND MOMENT EQUATIONS FOR OSCILLAT- 
ING AIRFOILS IN AN INFINITE UNSTAGGERED 
CASCADE. Alexander Mendelson and Robert W. 
Carroll. October 1954. 46p. diagrs., 3 tabs. 
(NACA TN 3263) 



A THEORETICAL INVESTIGATION OF THE 
SHORT-PERIOD DYNAMIC LONGITUDINAL 
STABILITY OF AIRPLANE CONFIGURATIONS 
HAVING ELASTIC WINGS OF 0° TO 60° SWEEP- 
BACK. Milton D. McLaughlin. December 1954. 
39p. diagrs., 2 tabs. (NACA TN 3251) 



DESCRIPTION AND ANALYSIS OF A ROCKET - 
VEHICLE EXPERIMENT ON FLUTTER INVOLVING 
WING DEFORMATION AND BODY MOTIONS. H. J. 
Cunningham and R. R. Lundstrom. January 1955. 
26p. diagrs., photos., 2 tabs. (NACA TN 3311. 
Formerly RM L50I29) 



A SIMPLIFIED METHOD FOR CALCULATING 
AEROELASTIC EFFECTS ON THE ROLL OF AIR- 
CRAFT. John M. Hedgepeth, Paul G. Waner, Jr. 
and Robert J. Kell. March 1955. 26p. diagrs., 
4 tabs. (NACA TN 3370) 



THE EFFECT OF CONTROL STIFFNESS AND FOR- 
WARD SPEED ON THE FLUTTER OF A 1/10-SCALE 
DYNAMIC MODEL OF A TWO-BLADE JET -DRIVEN 
HELICOPTER ROTOR. George W. Brooks and 
Maurice A. Sylvester. April 1955. 38p. diagrs., 
photo., 3 tabs. (NACA TN 3376) 



METHOD OF CONTROLLING STIFFNESS PROPER- 
TIES OF A SOLID-CONSTRUCTION MODEL WING. 
Norman S. Land and Frank T. Abbott, Jr. April 
1955. 2lp. diagrs., photos., tab. (NACA TN 3423) 



AERODYNAMICS 109 



Parachutes 
(I.IO) 



SUMMARY OF RESULTS OF TUMBLING INVESTI- 
GATIONS MADE IN THE LANGLEY 20-FOOT FREE- 
SPINNING TUNNEL ON 14 DYNAMIC MODELS. 
Ralph W. Stone, Jr. and Robert L. Bryant. 
December 31, 1948. 91p. diagrs., photos., 23 tabs. 
(NACA RM L8J28) 



AN INVESTIGATION OF THE SPIN, RECOVERY, 
AND TUMBLING CHARACTERISTICS OF A 1/20- 
SCALE MODEL OF THE NORTHROP X-4 AIRPLANE. 
Lawrence J. Gale, Ira P. Jones, Jr. and Jack H. 
Wilson. January 4, 1950. 27p. diagrs., photos., 4 
tabs. (NACA RM L9K28) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF VARIOUS ASYMMETRIC CANOPY MODIFICA- 
TIONS ON THE BEHAVIOR OF DESCENDING PARA- 
CHUTES. Stanley H. Scher. February 1952. 20p. 
diagrs., photos., tab. (NACA RM L51J18) 



WIND-TUNNEL INVESTIGATION OF THE BE- 
HAVIOR OF PARACHUTES IN CLOSE PROXIMITY 
TO ONE ANOTHER. Stanley H. Scher. August 
1953. 12p. photos. (NACA RM L53G07) 




HYDRODYNAMICS 
(2) 



HYDRODYNAMICS HI 



HYDRODYNAMICS 



(2) 



AVERAGE SKIN-FRICTION DRAG COEFFICIENTS 
FROM TANK TESTS OF A PARABOLIC BODY OF 
REVOLUTION (NACA RM-10). Elmo J. Mottard and 
J. Dan Loposer. 1954. 11, Vp. dlagrs., photos. 
(NACA Rept. 1161. Formerly TN 2854) 



THE HYDRODYNAMIC CHARACTERISTICS OF AN 
ASPECT -RATIO-0.125 MODIFIED RECTANGULAR. 
FLAT PLATE OPERATING NEAR A FREE WATER 
SURFACE. John A. Ramsen and Victor L. Vaughan, 
Jr. October 1954. 32p. dlagrs. (NACA TN 3249) 



HYDRODYNAMIC TARES AND INTERFERENCE 
EFFECTS FOR A 12-PERCENT -THICK SURFACE- 
PIERCING STRUT AND AN ASPECT -RATIO-0.25 
LIFTING SURFACE. John A. Ramsen and Victor L. 
Vaughan, Jr. April 1955. 20p. dlagrs. (NACA 
TN 3420) 



112 HY DROD YNAMICS 



Theory 

(2.1) 



A THEORETICAL AND EXPERIMENTAL INVESTI- 
GATION OF THE UFT AND DRAG CHARACTERIS- 
TICS OF A HYDROFOIL AT SUBCRITICAL AND 
SUPERCRITICAL SPEEDS. Kenneth L. WadUn, 
Charles L. Shuford, Jr. and John R. McGehee. July 
1952. 53p. diagrs., photo., tab. (NACA 
RM L52D23a) 

THEORY AND PROCEDURE FOR DETERMINING 
LOADS AND MOTIONS IN CHINE -IMMERSED 
HYDRODYNAMIC IMPACTS OF PRISMATIC 
BODIES. Emanuel Schnitzer. 1953. 11, 29p. 
diagrs. (NACA Rept. 1152. Formerly TN 2813) 

EXPERIMENTAL INVESTIGATION OF THE FLOW 
FIELD BEHIND AN ASPECT-RATIO-10 HYDROFOIL 
NEAR THE WATER SURFACE. Arthur W. Carter 
and Roger V. Butler. February 1953. 31p. diagrs., 
photos., tab. (NACA RM L52L11) 



A REVIEW OF PLANING THEORY AND EXPERI- 
MENT WITH A THEORETICAL STUDY OF PURE- 
PLANING LIFT OF RECTANGULAR FLAT PLATES. 
Charles L. Shuford, Jr. August 1954. 34p. diagrs. 
(NACA TN 3233) 



THE HYDRODYNAMIC CHARACTERISTICS OF AN 
ASPECT-RATIO-0.125 MODIFIED RECTANGULAR 
FLAT PLATE OPERATING NEAR A FREE WATER 
SURFACE. John A. Ramsen and Victor L. Vaughan, 
Jr. October 1954. 32p. diagrs. (NACA TN 3249) 



ANALYTIC DETERMINATION OF THE DISCHARGE 
COEFFICIENTS OF FLOW NOZZLES. Frederick S. 
Simmons. April 1955. 15p. diagrs. (NACA 
TN 3447) 



HYDRODYNAMICS ll3 



General Arrangement Studies 

(2.2) 



PRELIMINARY TAMC TESTS OF NACA HYDRO- 
SKIS FOR HIGH-SPEED AIRPLANES. John R. 
Dawson and Kenneth L. Wadlin. November 26, 1947. 
19p. diagrs., photos. (NACA RM L7I04) 



TANK SPRAY TESTS OF A JET-POWERED MODEL 
FITTED WITH NACA HYDRO-SKIS. Kenneth L. 
Wadlin and John A. Ramsen. July 22, 1948. 19p. 
diagrs., photos. (NACA RM L8B18) 



THE EFFECT OF REAR CHINE STRIPS ON THE 
TAKE-OFF CHARACTERISTICS OF A HIGH-SPEED 
AIRPLANE FITTED WITH NACA HYDRO-SKIS. 
John A. Ramsen. March 17, 1949. 7p. diagrs., 
photo. (NACA RM L9B10a) 



A PRELIMINARY INVESTIGATION OF THE STATIC 
AND DYNAMIC LONGITITOINAL STABILITY OF A 
GRUMBERG HYDROFOIL SYSTEM. Norman S. 
Land, DerriU B. Chambliss and William W. Petynia. 
September 1952. 48p. diagrs., photos. (NACA 
RM L52D15) 

A REVIEW OF PLANING THEORY AND EXPERI- 
MENT WITH A THEORETICAL STUDY OF PURE- 
PLANING LIFT OF RECTANGULAR FLAT PLATES. 
Charles L. Shuford, Jr. August 1954. 34p. diagrs. 
(NACA TN 3233) 



114 HYDRODYNAMICS 



Seaplane Hull Variables 
(2.3) 



PRELIMINARY WIND-TUNNEL INVESTIGATION AT 
fflGH -SUBSONIC SPEEDS OF PLANING-TAIL, 
BLENDED, AND AIRFOIL-FOREBODY SWEPT 
HULLS. John M. Riebe and Richard G. MacLeod. 
September 12, 1949. 33p. diagrs., photos., 3 tabs. 
(NACA RM L9D01) 



HYDRODYNAMIC FORCE CHARACTERISTICS OF A 
STREAMLINE FUSELAGE MODIFIED BY EITHER 
BREAKER STRIPS OR ROWS OF AIR JETS- SIMU- 
LATING CHINES. Bernard Weinflash, Charles L. 
Shuford, Jr. and Kenneth W. Christopher. 
February 21, 1950. 45p. diagrs., photos. (NACA 
RM L9L21a) 



INVESTIGATION OF THE HYDRODYNAMIC STA- 
BILITY AND RESISTANCE OF TWO STREAMLINE 
FUSELAGES. Bernard Weinflash and Charles L. 
Shuford, Jr. April 1952. 32p. diagrs., photos., 
tab. (NACA RM L52B11) 



LENGTH-BEAM RATIO 
(2.3,1) 



THEORY AND PROCEDURE FOR DETERMINING 
LOADS AND MOTIONS IN CHINE -IMMERSED 
HYDRODYNAMIC IMPACTS OF PRISMATIC 
BODIES. Emanuel Schnitzer. 1953. ii, 29p. 
diagrs. (NACA Rept. 1152. Formerly TN 2813) 



A REVIEV.' OF PLANING THEORY AND EXPERI- 
MENT WITH A THEORETICAL STUDY OF PURE- 
PLANING LIFT OF RECTANGULAR FLAT PLATES. 
Charles L. Shuford, Jr. August 1954. 34p. diagrs. 
(NACA TN 3233) 



DEAD RISE 
(2.3.2) 



THEORY AND PROCEDURE FOR DETERMINING 
LOADS AND MOTIONS IN CHINE -IMMERSED 
HYDRODYNAMIC IMPACTS OF PRISMATIC 
BODIES. Emanuel Schnitzer. 1953. ii, 29p. 
diagrs. (NACA Rept. 1152. Formerly TN 2813) 



STEPS 
(2.3.3) 



THE EFFECT OF AIR JETS SIMULATING CHINES 
OR MULTIPLE STEPS ON THE HYDRODYNAMIC 
CHARACTERISTICS OF A STREAMLINE FUSELAGE. 
Bernard Weinflash. January 7, 1949. 37p. diagrs., 
photos., 2 tabs. (NACA RM L8J21) 



THE EFFECT OF AIR-JET AND STRIP MODIFI- 
CATIONS ON THE HYDRODYNAMIC CHARACTER- . 
ISTICS OF THE STREAMLINE FUSELAGE OF A 
TRANSONIC AIRPLANE. Bernard Weinflash, 
Kenneth W. Christopher and Charles L. Shuford, Jr. 
June 3, 1949. 32p. diagrs., photos. (NACA 
RM L9D20) 



CHINES 
(2.3.6) 



THE EFFECT OF AIR JETS SIMULATING CHINES 
OR MULTIPLE STEPS ON THE HYDRODYNAMIC 
CHARACTERISTICS OF A STREAMUNE FUSELAGE. 
Bernard Weinflash. January 7, 1949. 37p. diagrs., 
photos., 2 tabs. (NACA RM L8J21) 



PRELIMINARY TANK INVESTIGATION OF THE USE 
OF SINGLE MONOPLANE HYDROFOllS FOR HIGH- 
SPEED AIRPLANES. Douglas A. King and John A. 
Rockett. March 22, 1949. 35p. diagrs., photos., 6 
tabs. (NACA RM L9A17) 



THE EFFECT OF AIR-JET AND STRIP MODIFI- 
CATIONS ON THE HYDRODYNAMIC CHARACTER- 
ISTICS OF THE STREAMLINE FUSELAGE OF A 
TRANSONIC AIRPLANE. Bernard Weinflash, 
Kenneth W. Christopher and Charles L. Shuford, Jr. 
June 3, 1949. 32p. diagrs., photos. (NACA 
RM L9D20) 



HYDRODYNAMIC FORCE CHARACTERISTICS OF A 
STREAMLINE FUSELAGE MODIFIED BY EITHER 
BREAKER STRIPS OR ROWS OF AIR JETS SIMU- 
LATING CHINES. Bernard Weinflash, Charles L. 
Shuford, Jr. and Kenneth W. Christopher. 
February 21, 1950. 45p. diagrs., photos. (NACA 
RM L9L21a) 



HYDRODYNAMICS 115 



Planing Surfaces 
(2.6) 



PRELIMINARY TANK TESTS OF NACA HYDRO- 
SKIS FOR HIGH-SPEED AIRPLANES. John R. 
Dawson and Kenneth L. Wadtin. November 26, 1947. 
19p. dlagrs., photos. (NACA RM L7I04) 



TANK SPRAY TESTS OF A JET-POWERED MODEL 
FITTED WITH NACA HYDRO-SKIS. Kenneth L. 
Wadlin and John A. Ramsen. July 22, 1948. 19p. 
diagrs., photos. (NACA RM L8B18) 



THE EFFECT OF REAR CHINE STRIPS ON THE 
TAKE-OFF CHARACTERISTICS OF A HIGH-SPEED 
AIRPLANE FITTED WITH NACA HYDRO-SKK. 
John A. Ramsen. March 17, 1949. 7p. diagrs., 
photo. (NACA RM L9B10a) 



A REVIEW OF PLANING THEORY AND EXPERI- 
MENT WITH A THEORETICAL STUDY OF PURE- 
PLANING UFT OF RECTANGULAR FLAT PLATES. 
Charles L. Shuford, Jr. August 1954. 34p. diagrs. 
(NACA TN 3233) 



116 HYDRODYNAMICS 



Hydrofoils 
(2.7) 



PREUMINARY TANK INVESTIGATION OF THE USE 
OF SINGLE MONOPLANE HYDROFOILS FOR HIGH- 
SPEED AIRPLANES. Douglas A. King and John A. 
Rockett. March 22, 1949. 35p. dlagrs., photos., 6 
tabs. (NACA RM L9A17) 



THE EFFECT OF END PLATES, END STRUTS, 
AND DEPTH OF SUBMERGENCE ON THE CHAR- 
ACTERISTICS OF A HYDROFOIL. Kenneth L. 
Wadlin, Rudolph E. Fontana and Charles L. Shuford, 
Jr. April 12, 1951. 84p. dlagrs., photos. (NACA 
RM L51B13) 



A THEORETICAL AND EXPERIMENTAL INVESTI- 
GATION OF THE LIFT AND DRAG CHARACTERIS- 
TICS OF A HYDROFOIL AT SUBCRITICAL AND 
SUPERCRITICAL SPEEDS. Kenneth L. Wadlin, 
Charles L. Shuford, Jr. and John R. McGehee. July 
1952. 53p. diagrs., photo., tab. (NACA 
RM L52D23a) 

A PRELIMINARY INVESTIGATION OF THE STATIC 
AND DYNAMIC LONCHTUDINAL STABILITY OF A 
GRUMBERG HYDROFOIL SYSTEM. Norman S. 
Land, Derrill B. Chambliss and William W. Petynia. 
September 1952. 48p. diagrs., photos. (NACA 
RM L52D15) 



EFFECTS OF SWEEPBACK AND TAPER ON THE 
FORCE AND CAVITATION CHARACTERISTICS OF 
ASPECT-RATIO-4 HYDROFOILS. Douglas A. 
King and Norman S. Land. December 1952. 61p. 
diagrs. , photos. , tab. (NACA RM L52J10) 



THEORY AND PROCEDURE FOR DETERMINING 
LOADS AND MOTIONS IN CHINE -IMMERSED 
HYDRODYNAMIC IMPACTS OF PRISMATIC 
BODIES. Emanuel Schnitzer. 1953. ii, 29p. 
diagrs. (NACA Rept. 1152. Formerly TN 2813) 



EXPERIMENTAL INVESTIGATION OF THE FLOW 
FIELD BEHIND AN ASPECT -RATIO-10 HYDROFOIL 
NEAR THE WATER SURFACE. Arthur W. Carter 
and Roger V. Butler. February 1953. 31p. diagrs., 
photoe., tab. (NACA RM L52L11) 



THE HYDRODYNAMIC CHARACTERISTICS OF AN 
ASPECT-RATIO-0.125 MODIFIED RECTANGULAR 
FLAT PLATE OPERATING NEAR A FREE WATER 
SURFACE. John A. Ramsen and Victor L. Vaughan, 
Jr. October 1954. 32p. dlagrs. (NACA TN 3249) 



HYDRODYNAMIC TARES AND INTERFERENCE 
EFFECTS FOR A 12-PERCENT-THICK SURFACE- 
PIERCING STRUT AND AN ASPECT-RATIO-0.25 
LIFTING SURFACE. John A. Ramsen and Victor L. 
Vaughan, Jr. April 1955. 20p. diagrs. (NACA 
TN 3420) 



HYDRODYNAMICS 117 



Surface Craft 

(2.8) 



A PRELIMINARY INVESTIGATION OF THE STATIC 
AND DYNAMIC LONGITUDINAL STABILITY OF A 
GRUMBERG HYDROFOIL SYSTEM. Norman S. 
Land, Derrill B. Chambliss and WUliam W. Petynia. 
September 1952. 48p. diagrs., photos. (NACA 
RM L52D15) 



118 HYDRODYNAMICS 



Stability and Control 
(2.10) 



LONGITUDINAL 
(2.10.1) 



PRELIMINARY TANK INVESTIGATION OF THE USE 
OF SINGLE MONOPLANE HYDROFOII^ FOR HIGH- 
SPEED AIRPLANES. Douglas A. King and John A. 
Rockett. March 22, 1949. 35p. dlagrs., photos., 6 
tabs. (NACA RM L9A17) 



INVESTIGATION OF THE HYDRODYNAMIC STA- 
BILITY AND RESISTANCE OF TWO STREAMLINE 
FUSELAGES. Bernard WeinAash and Charles L. 
Shuford, Jr. AprU 1952. 32p. diagrs., photos., 
tab. (NACA RM L52B11) 



A PRELIMINARY INVESTIGATION OF THE STATIC 
AND DYNAMIC LONOTUDINAL STABILITY OF A 
GRUMBERG HYDROFOIL SYSTEM. Norman S. 
Land, Derrill B. ChambUss and William W. Fetynia. 
September 1952. 48p. diagrs., photos. (NACA 
RM L52D15) 




PROPULSION 
(3) 



PROPULSION 119 



PROPULSION 
(3) 



INVESTIGATION OF JET -ENGINE NOISE REDUC- 
TION BY SCREENS LOCATED TRANSVERSELY 
ACROSS THE JET. Edmund E. Callaghan and 
Willard D. Coles. May 1955. 27p. dlagrs., photos., 
tab. (NACA TN 3452) 



120 PROPULSION 



Complete Systems 
(3.1) 



METHOD AND GRAPHS FOR THE EVALUATION OF 
AIR-INDUCTION SYSTEMS. George B. Brajnikoff. 
1953. il, 22p. dlagrs., tab. (NACA Rept. 1141. 
Formerly TN 2697) 

A METHOD FOR EVALUATING THE EFFECTS OF 
DRAG AND INLET PRESSURE RECOVERY ON 
PROPULSION-SYSTEM PERFORMANCE. Emil J. 
Krerazler. August 1954. 21p. diagrs. (NACA 
TN 3261) 

RECIPROCATING ENGINES 
(3.1.1) 

MECHANISM OF START AND DEVELOPMENT OF 
AIRCRAFT CRASH FIRES. I. Irving Pinkel, G. 
Merrltt Preston and Gerald J. Pesman. 1953. iii, 
52p. diagrs., photos., 2 tabs. (NACA Rept. 1133. 
Formerly RM E52F06) 

TURBOJET ENGINES 
(3.1.3) 

EFFECT OF INLET TEMPERATURE AND HUMID- 
ITY ON THRUST AUGMENTATION OF TURBOJET 
ENGINE BY COMPRESSOR-INLET INJECTION. 
Thomas B. Shilllto and James L. Harp, Jr. July 3, 

1950. 46p. diagrs., photos. (NACA RM E50D19) 

CARBON DEPOSITION OF SEVERAL SPECIAL 
TURBOJET-ENGINE FUELS. Jerrold D. Wear and 
James W. Useller. April 10, 1951. 15p. photos., 
diagr., tab. {NACA RM E51C02) 

EXPERIMENTAL INVESTIGATION OF TYPICAL 
CONSTANT- AND VARIABLE -AREA EXHAUST 
NOZZLES AND EFFECTS ON AXIAL-FLOW 
TURBOJET -ENGINE PERFORMANCE. Lewis E. 
Wallner and John T. Wintler. July 1951. 43p. 
diagrs., photos. (NACA RM E51D19) 

INVESTIGATION OF MECHANISMS OF BLADE 
FAILURE OF FORGED HASTELLOY B AND CAST 
STELLITE 21 TURBINE BLADES IN TURBOJET 
ENGINE. C. Yaker, C. F. Robards and F. B. 
Garrett. August 1951. 41p. diagrs., photos., 2 tabs. 
(NACARM E51D16) 

ALTITUDE -IGNITION LIMIT OF A TURBOJET 
ENGINE USING A CONDENSER -DISCHARGE 
IGNITION SYSTEM. John C. Armstrong. October 

1951. 5p. diagrs. (NACA RM E51F11) 

EXPERIMENTAL INVESTIGATION OF THE VIBRA- 
TION CHARACTERISTICS OF FOUR DESIGNS OF 
TURBINE BLADES AND OF THE EFFECT PRO- 
DUCED BY VARYING THE AXIAL SPACING 
BETWEEN NOZZLE BLADES AND TURBINE 
BLADES. W. C. Morgan and C. R. Morse. 
February 1952. 28p. diagrs., photos., tab. (NACA 
RM E51J25) 

INVESTIGATION OF ENGINE PERFORMANCE AND 
HIGH-TEMPERATURE PROPERTIES OF 
PRECISION-CAST TURBINE BLADES OF HIGH- 
CARBON STELUTE 21 AND CONTROL LED -GRAIN - 
SIZE STELLITE 21. Charles Yaker, Floyd B. 
Garrett and Paul F. Sikora. June 1952. 38p. 
diagrs., photos., 6 tabs. (NACA RM E52D10) 



INVESTIGATION OF POWER EXTRACTION CHAR- 
ACTERISTICS AND BRAKING REQUIREMENTS OF A 
WINDMILLING TURBOJET ENGINE. Curtis L. 
Walker and David B. Fenn. July 1952. 31p. diagrs., 
tab. (NACA BM E52D30) 

BEHAVIOR OF FORGED S-816 TURBINE BLADES 
IN STEADY-STATE OPERATION OF J33-9 TURBO- 
JET ENGINE WITH STRESS-RUPTURE AND 
METALLOGRAPHIC EVALUATIONS. F. B. Garrett, 
C. A. Gyorgak and J. W. Weeton. February 1953. 
29p. diagrs., photos., 3 tabs. (NACA RME52L17) 

COMPARISON OF THEORETICALLY AND EXPERI- 
MENTALLY DETERMINED EFFECTS OF OXIDE 
COATINGS SUPPLIED BY FUEL ADDITIVES ON 
UNCOOLED TURBINE-BLADE TEMPERATURE 
DURING TRANSIENT TURBOJET -ENGINE OPERA- 
TION. Louis J. Schafer, Jr., Francis S. Stepka 
andW. Byron Brown. March 1953. 45p. photos., 
diagrs., tab. (NACA RM E53A19) 

THE DESIGN OF BRITTLE -MATERIAL BLADE 
ROOTS BASED ON THEORY AND RUPTURE TESTS 
OF PLASTIC MODELS. Andre J. Meyer, Jr., 
Albert Kaufman ami WiUiam C. Caywood. 
AprU 6, 1953. 45p. diagrs., photos., tab. (NACA 
RM E53C12) 

THE NEAR NOBE FIELD OF STATIC JETS AND 
SOME MODEL STUDIES OF DEVICES FOR NOISE 
REDUCTION. Leslie W. Lassiter and Harvey H. 
Hubbard. July 1954. 38p. diagrs., photos. (NACA 
TN3187) 

TRANSVERSE OSCILLATIONS IN A CYLINDRICAL 
COMBUSTION CHAMBER. Franklin K. Moore and 
Stephen H. Maslen. October 1954. 25p. diagrs. 
(NACA TN 3152) 

METHODS FOR RAPID GRAPHICAL EVALUATION 
OF COOLED OR UNCOOLED TURBOJET AND 
TURBOPROP ENGINE OR COMPONENT PERFORM- 
ANCE (EFFECTS OF VARIABLE SPECIFIC HEAT 
INCLUDED). Jack B. Esgar and Robert R. Ziemer. 
January 1955. 45p. diagrs. (NACA TN 3335) 

INGESTION OF FOREIGN OBJECTS INTO TURBINE 
ENGINES BY VORTICES. Lewis A. Rodert and 
Floyd B. Garrett. February 1955. 23p. diagrs., 
photos. (NACA TN 3330) 

A SELF-EXCITED, ALTERNATING-CURRENT, 
CONSTANT -TEMPERATURE HOT-WIRE ANEMOM- 
ETER. Charles E. Shepard. April 1955. 29p. 
diagrs., photos. (NACA TN 3406) 

INVESTIGATION OF JET-ENGINE NOISE REDUC- 
TION BY SCREENS LOCATED TRANSVERSELY 
ACROSS THE JET. Edmund E. Callaghan and 
Wlllard D. Coles. May 1955. 27p. diagrs., photos., 
tab. (NACA TN 3452) 

TURBO-PROPELLER ENGINES 



(3.1.4) 



ANALYSIS OF EXPERIMENTAL SEA-LEVEL 
TRANSIENT DATA-AND ANALOG METHOD OF 
OBTAINING ALTITUDE RESPONSE FOR TURBINE- 
PROPELLER ENGINE WITH RELAY-TYPE SPEED 
CONTROL. George Vasu and George J. Pack. 
May 17, 1951. 28p. diagrs., photo. (NACA 
BM E51D26) 



PROFUL.SION 
COMPLETE SYSTEMS (3. 1) 



121 



Turbo -Propeller Engines (Cont. ) 

CORRELATION OF ANALOG SOLUTIONS WITH EX- 
PERIMENTAL SEA-LEVEL TRANSIENT DATA FOR 
CONTROLLED TURBINE -PROPELLER ENGINE, 
INCLUDING ANALOG RESULTS AT ALTITUDES. 
James Lazar and Wilfred L. DeRocher, Jr. August 
1951. 36p. dlagrs. (NACA RM E51B08) 

INVESTIGATION OF DYNAMIC CHARACTERISTICS 
OF A TURBINE-PROPELLER ENGINE. Frank L. 
Oppenhelmer and James R. Jacques. September 
1951. 22p. dlagrs., tab. (NACA RM E51F15) 

A METHOD FOR ESTIMATING SPEED RESPONSE 
OF GAS-TURBINE ENGINES. Harold Gold and 
Solomon Rosenzweig. January 1952. 26p. dlagrs. 
(NACA RM E51K21) 

METHODS FOR RAPID GRAPHICAL EVALUATION 
OF COOLED OR UNCOOLED TURBOJET AND 
TURBOPROP ENGINE OR COMPONENT PERFORM- 
ANCE (EFFECTS OF VARIABLE SPECIFIC HEAT 
INCLUDED). Jack B. Esgar and Robert R. Zlemer. 
January 1955. 45p. dlagrs. (NACA TN 3335) 

ANALYTICAL DETERMINATION OF EFFECT OF 
WATER INJECTION ON POWER OUTPUT OF 
TURBINE -PROPELLER ENGINE. Albert O. Ross 
and Merle C. Huppert. March 1955. 29p. dlagrs. 
(NACA TN 3403. Formerly RM E9H17) 



RAM-JET ENGINES 
(3.1.7) 



FLIGHT TESTS OF A TWO-DIMENSIONAL WEDGE 
DIFFUSER AT TRANSONIC AND SUPERSONIC 
SPEEDS. M. A. Faget. August 11, 1948. 21p. 
diagrs., photos. (NACA RM L8E27) 

AN ANALYSIS OF BUZZING IN SUPERSONIC RAM 
JETS BY A MODIFIED ONE -DIMENSIONAL NON- 
STATIONARY WAVE THEORY. Robert L. Trlmpl. 
March 1952. 72p. dlagrs., photos. (NACA 
RM L52A18) 

A THEORY FOR STABILITY AND BUZZ PULSATION 
AMPLITUDE IN RAM JETS AND AN EXPERIMEN- 
TAL INVESTIGATION INCLUDING SCALE EFFECTS. 
Robert L. Trlmpl. October 1953. 75p. diagrs., 
photos., 3 tabs. (NACA RM L53G28) 

TRANSVERSE OSCILLATIONS IN A CYLINDRICAL 
COMBUSTION CHAMBER. Franklin K. Moore and 
Stephen H. Maslen. October 1954. 25p. diagrs. 
(NACA TN 3152) 



ROCKET ENGINES 
(3.1.8) 



DETERMINATION OF FLAME TEMPERATURES 
FROM 2000° TO 3000° K BY MICROWAVE ABSORP- 
TION. Perry W. Kuhns. August 1954. 48p. 
diagrs., photo., 2 tabs. (NACA TN 3254) 

SOME MEASUREMENTS OF NOISE FROM THREE 
SOLID-FUEL ROCKET ENGINES. Leslie W. 
Lassiter and Robert H. Heitkotter. December 1954. 
21p. diagrs. (NACA TN 3316) 



IGNITION-DELAY DETERMINATIONS OF 
FURFURYL ALCOHOL AND MIXED BUTYL 
MERCAPTANS WITH VARIOUS WHITE FUMING 
NITRIC ACIDS USING MODIFIED OPEN-CUP AND 
SMALL-SCALE ROCKET ENGINE APPARATUS. 
Dezso J. Ladanyi, Riley O. Miller and Glen 
Hennings. February 1955. 17p. diagrs., photos., 
4 tabs. (NACA RM E53E2g) 

JET-DRIVEN ROTORS 
(3.1.9) 

DESCRIPTION AND INVESTIGATION OF A 
DYNAMIC MODEL OF THE XH-17 TWO-BLADE 
JET-DRIVEN HELICOPTER. George W. Brooks and 
Maurice A. Sylvester. March 14, 1951. 49p. 
dlagrs., photos., 6 tabs. (NACA RM L50I21) 

THE EFFECT OF CONTROL STIFFNESS AND FOR- 
WARD SPEED ON THE FLUTTER OF A 1/10-SCALE 
DYNAMIC MODEL OF A TWO-BLADE JET -DRIVEN 
HELICOPTER ROTOR. George W. Brooks and 
Maurice A. Sylvester. April 1955. 38p. dlagrs., 
photo., 3 tabs. (NACA TN 3376) 

A DYNAMIC-MODEL STUDY OF THE EFFECT OF 
ADDED WEIGHTS AND OTHER STRUCTURAL VAR- 
IATIONS ON THE BLADE BENDING STRAINS OF AN 
EXPERIMENTAL TWO-BLADE JET -DRIVEN HELI- 
COPTER IN HOVERING AND FORWARD FLIGHT. 
John Locke McCarty and George W. Brooks. May 
1955. i, 47p. diagrs., photo., 6 tabs. (NACA 
TN 3367) 



NUCLEAR- ENERGY SYSTEM 
(3.1.10) 



SLOWING -DOWN DISTRIBUTION TO INDIUM 
RESONANCE OF NEUTRONS FROM A Ra-a-Be 
SOURCE IN WATER-IRON MIXTURES. Daniel 
Fieno. November 1954. 16p. diagrs., photo., 
2 tabs. (NACA RM E54H04) 

REVIEW OF EXPERIMENTAL INVESTIGATIONS OF 
LIQUID-METAL HEAT TRANSFER. Bernard 
Lubarsky and Samuel J. Kaufmann. March 1955. 
115p. diagrs., tab. (NACA TN 3336) 



COMPARISON 
OF ENGINE TYPES 

(3.1.12) 



COMPARISON OF HOVERING PERFORMANCE OF 
HELICOPTERS POWERED BY JET -PROPULSION 
AND RECIPROCATING ENGINES. Virginia L. 
Brightwell, Max D. Peters and J. C. Sanders. 
June 11, 1948. 39p. diagrs., 3 tabs. (NACA 
RM E7K21) 



METHOD AND GRAPHS FOR THE EVALUATION OF 
AIR -INDUCTION SYSTEMS. George B. BrajnikoH. 
1953. il, 22p. diagrs., tab. (NACA Rept. 1141. 
Formerly TN 2697) 



122 PROPULSION 



Control of Engines 

(3.2) 



ANALYSIS OF EXPERIMENTAL SEA-LEVEL 
TRANSIENT DATA AND ANALOG METHOD OF 
OBTAINING ALTITUDE RESPONSE FOR TURBINE - 
PROPELLER ENGINE WITH RELAY-TYPE SPEED 
CONTROL. George Vasu and George J. Pack. 
May 17, 1951. 28p. diagrs., photo. (NACA 
RM E51D26) 

INVESTIGATION OF DYNAMIC CHARACTERISTICS 
OF A TURBINE -PROPELLER ENGINE. Frank L. 
Oppenheimer and James R. Jacques. September 
1951. 22p. diagrs., tab. (NACA RM E51F15) 

A METHOD FOR ESTIMATING SPEED RESPONSE 
OF GAS-TUHBINE ENGINES. Harold Gold and 
Solomon Rosenzweig. January 1952. 26p. diagrs. 
(NACA RM E51K21) 



DESIGN AND PERFORMANCE OF THROTTLE- 
TYPE FUEL CONTROLS FOR ENGINE DYNAMIC 
STUDIES. Edward W. Otto, Harold Gold and Kirby 
W. Hiller. April 1955. 39p. diagrs., photo. 
(NACA TN 3445) 



CONTROL OF 
TURBOJET ENGINES 

(3.2.2) 



COMPARISON OF PERFORMANCE OF AN-F-58 
AND AN-F-32 FUELS IN J33-A-23 TURBOJET 
ENGINE. H. D. Wilsted and J. C. Armstrong. 
June 2, 1949, 33p. photos., diagrs., tab. (NACA 
RM E8K24) 

INSTRUMENTATION FOR RECORDING TRANSIENT 
PERFORMANCE OF GAS-TURBINE ENGINES AND 
CONTROL SYSTEMS. Gene J. Delio and Glennon V 
Schwent. June 27, 1951. 27p. diagrs., photos. 
(NACA RM E51D27) 

DYNAMIC RESPONSE OF TURBINE -BLADE 
TEMPERATURE TO EXHAUST -GAS TEMPERA- 
TURE FOR GAS -TURBINE ENGINES. Richard Hood 
and William E. Phillips, Jr. February 1952. 41p. 
photos., diagrs. (NACA RM E52A14) 



CONTROL OF 
TURBINE-RAM-JET ENGINES 
(3.2.3) 



DYNAMIC RESPONSE OF TURBINE -BLADE 
TEMPERATURE TO EXHAUST -GAS TEMPERA- 
TURE FOR GAS -TURBINE ENGINES. Richard Hood 
and William E. Phillips, Jr. February 1952. 41p. 
photos., diagrs. (NACA RM E52A14) 



CONTROL OF 
TURBINE-PROPELLER ENGINES 
(3.2.4) 



ANALYSIS OF EXPERIMENTAL SEA-LEVEL 
TRANSIENT DATA AND ANALOG METHOD OF 
OBTAINING ALTITUDE RESPONSE FOR TURBINE - 
PROPELLER ENGINE WITH RELAY -TYPE SPEED 
CONTROL. George Vasu and George J. Pack. 
May 17, 1951. 28p. diagrs., photo. (NACA 
RM E51D26) 



CORRELATION OF ANALOG SOLUTIONS WITH EX- 
PERIMENTAL SEA-LEVEL TRANSIENT DATA FOR 
CONTROLLED TURBINE -PROPELLER ENGINE, 
INCLUDING ANALOG RESULTS AT ALTITUDES. 
James Lazar and Wilfred L. DeRocher, Jr. August 
1951. 36p. diagrs. (NACA RM E51B08) 

INVESTIGATION OF DYNAMIC CHARACTERISTICS 
OF A TURBINE -PROPELLER ENGINE. Frank L. 
Oppenheimer and James R. Jacques. September 
1951. 22p. diagrs., tab. (NACA RM E51F15) 

PRELIMINARY INVESTIGATION OF THE CONTROL 
OF A GAS-TURBINE ENGINE FOR A HELICOPTER. 
Richard P. Krebs. September 1951. 13p. diagrs. 
(NACA RM E51F19) 



A METHOD FOR ESTIMATING SPEED RESPONSE 
OF GAS-TURBINE ENGINES. Harold Gold and 
Solomon Rosenzweig. January 1952. 26p. diagrs. 
(NACA RM E51K21) 

DYNAMIC RESPONSE OF TURBINE -BLADE 
TEMPERATURE TO EXHAUST -GAS TEMPERA- 
TURE FOR GAS-TURBINE ENGINES. Richard Hood 
and William E. Phillips, Jr. February 1952. 41p. 
photos., diaars. (NACA RM E52A14) 



PROPULSION 123 



Auxiliary Booster Systems 

(3.3) 



GAS TURBINES 
(3.3.2) 

LIQUID INJECTION 
(3.3.2.1) 

EFFECT OF INLET TEMPERATURE AND HUMID- 
ITY ON THRUST AUGMENTATION OF TURBOJET 
ENGINE BY COMPRESSOR-INLET INJECTION. 
Thomas B. Shillito and James L. Harp, Jr. July 3, 
1950. 46p. diagrs., photos. (NACA RM E50D19) 

ANALYTICAL DETERMINATION OF EFFECT OF 
WATER INJECTION ON POWER OUTPUT OF 
TURBINE -PROPELLER ENGINE. Alberto. Ross 
and Merle C. Huppert. March 1955. 29p. diagrs. 
(NACA TN 3403. Formerly RM E9H17) 

AFTERBURNING 
(3.3.2.2) 

EFFECT OF FUEL VOLATILITY ON PERFORM- 
ANCE OF TAIL-PIPE BURNER. Zelmar Barson 
and Arthur F. Sargent, Jr. April 30, 1951. 18p. 
diagrs., tab. (NACA RM E51C14) 



EXPERIMENTAL INVESTIGATION OF TYPICAL 
CONSTANT- AND VASLABLE-AREA EXHAUST 
NOZZLES AND EFFECTS ON AXIAL-FLOW 
TURBOJET -ENGTOE PERFORMANCE. Lewis E. 
Wallner and John T. Wlntler. July 1951. 43p. 
diagrs., photos. (NACA RM E51D19) 

INVESTIGATION OF NOISE FIELD AND VELOCITY 
PROFILES OF AN AFTERBURNING ENGINE. 
Warren J. North, Edmund E. Callaghan and Chester 
D. Lanzo. September 1954. 23p. diagrs., photos. 
(NACA RM E54G07) 

TRANSVERSE OSCILLATIONS IN A CYLINDRICAL 
COMBUSTION CHAMBER. Franklin K. Moore and 
Stephen H. Maslen. October 1954. 25p. diagrs. 
(NACA TN 3152) 



124 PROPULSION 



Fuels 
(3.4) 



CARBON DEPOSITION OF SEVERAL SPECIAL 
TURBOJET-ENGINE FUELS. Jerrold D. Wear and 
James W. Useller. April 10, 1951. 15p. photos., 
diagr., tab. {NACA RM E51C02) 

COMPARISON OF THEORETICALLY AND EXPERI- 
MENTALLY DETERMINED EFFECTS OF OXIDE 
COATINGS SUPPLIED BY FUEL ADDITIVES ON 
UNCOOLED TURBINE -BLADE TEMPERATURE 
DURING TRANSIENT TURBOJET -ENGINE OPERA- 
TION. Louis J. Schafer, Jr., Francis S. Stepka 
and W. Byron Brown. March 1953. 45p. photos., 
diagrs., tab. (NACA RM Ed3A19) 

BURNING TIMES OF MAGNESIUM RIBBONS IN 
VARIOUS ATMOSPHERES, kenneth P. Coffin. 
December 1954. 37p. diagrs., photos. (NACA 
TN 3332) 



PHYSICAL AND CHEMICAL 



PROPERTIES 
(3.4.2) 

ALTITUDE PERFORMANCE OF AN-F-58 FUELS IN 
J33-A-21 SINGLE COMBUSTOR. Ralph T. Dittrich 
and Joseph L. Jackson. April 8, 1949. 23p. 
diagrs., 2 tabs. (NACA RM E8L24) 

CARBON DEPOSITION FROM AN-F-58 FUELS IN A 
J33 SINGLE COMBUSTOR. Jerrold D. Wear and 
Howard W. Douglass. June 24, 1949. 27p. diagrs., 
photos., 2 tabs. (NACA RM E9D06) 

INVESTIGATION OF IGNITION CHARACTERISTICS 
OF AN-F-32 AND TWO AN-F-58a FUELS IN 
SINGLE CAN-TYPE TURBOJET COMBUSTOR. 
Warren D. Rayle and Howard W. Douglass. 
October 13, 1950. 25p. photos., diagrs., 2 tabs. 
(NACA RM E50H16a) 

COMBUSTION EFFICIENCY AND ALTITUDE OPER- 
ATIONAL LIMITS OF THREE LIQUID HYDRO- 
CARBON FUELS HAVING HIGH VOLUMETRIC 
ENERGY CONTENT IN A J33 SINGLE COMBUSTOR. 
Edward G. Strieker. November 6, 1950. 22p. 
diagrs., tab. (NACA RM E50H28) 

CARBON DEPOSITION OF SEVERAL SPECIAL 
TURBOJET-ENGINE FUELS. Jerrold D. Wear and 
James W. Useller. April 10, 1951. 15p. photos., 
dlagr., tab. (NACA RM E51C02) 

RELATIONS BETWEEN FUEL PROPERTIES AND 
COMBUSTION CARBON DEPOSITION. Edmund R. 
Jonash, Jerrold D. Wear and Robert R. Hibbard. 
April 1952. 67p. diagrs., 3 tabs. (NACA 
RM E52B14) 

PREDICTION OF FLAME VELOCITIES OF 
HYDROCARBON FLAMES. Gordon L. Dugger and 
Dorothy M. Simon. 1954. it. lOp. diagrs., 4 tabs. 
(NACA Rept. 1158. Formerly RM E52J13) 

FORMATION AND COMBUSTION OF SMOKE IN 
LAMINAR FLAMES. Rose L. Schalla, Thomas P. 
Clark and Glen E. McDonald. 1954. ii, 21p. 
diagrs., photos. (NACA Rept. 1186. Formerly 
RM E51E15; RM E52G24; RM £52122; RM E52I26; 
RM E53E05; RM E53J12; RM E54E03) 



INFRARED SPECTRA OF 47 DICYCLIC HYDRO- 
CARBONS. John H. Lamneck, Jr., Harold F. 
Hipsher and Virginia O. Fenn. June 1954. 34p. 
diagrs., 5 tabs. (NACA TN 3154) 

IGNITION-DELAY DETERMINATIONS OF 
FURFURYL ALCOHOL AND MIXED BUTYL 
MERCAPTANS WITH VARIOUS WHITE FUMING 
NITRIC ACIDS USING MODIFIED OPEN-CUP AND 
SMALL-SCALE ROCKET ENGINE APPARATUS. 
Dezso J. Ladanyi, Riley O. Miller and Glen 
Hennlngs. February 1955. 17p. diagrs., photos., 
4 tabs. (NACA RM E53E29) 

AN EVALUATION OF NON-NEWTONIAN FLOW IN 
PIPE LINES. Ruth N. Weltmann. February 1955. 
40p. diagrs., tab. (NACA TN 3397) 

A THERMAL EQUATION FOR FLAME QUENCHING. 
A. E. Potter, Jr. and A. L. Berlad. February 1955. 
18p. diagrs, tab. (NACA TN 3398) 

TEMPERATURE -COMPOSITION LIMITS OF SPON- 
TANEOUS EXPLOSION FOR NINE ALKYLSILANES 
WITH AIR AT ATMOSPHERIC PRESSURE. Rose L. 
Schalla and Glen E. McDonald. February 1955. 
13p. diagrs. (NACA TN 3405) 

CHAIN BREAKING AND BRANCHING IN THE 
ACTIVE-PARTICLE DIFFUSION CONCEPT OF 
QUENCHING. Frank E. Belles and A. L. Berlad. 
February 1955. 37p. diagrs, 3 tabs. (NACA 
TN 3409) 

EFFECT OF AMMONIA ADDITION ON LIMITS OF 
FLAME PROPAGATION FOR ISOOCTANE-AIR 
MIXTURES AT REDUCED PRESSURES AND ELE- 
VATED TEMPERATURES. Cleveland O'Neal, Jr. 
April 1955. 32p. diagrs., 3 tabs. (NACA TN 3446) 



RELATION TO ENGINE 

PERFORMANCE 

(3.4.3) 

ALTITUDE PERFORMANCE OF AN-F-58 FUELS IN 
J33-A-21 SINGLE COMBUSTOR. Ralph T. Dittrich 
and Joseph L. Jackson. April 8, 1949. 23p. 
diagrs., 2 tabs. (NACA RM E8L24) 

RELATIONS BETWEEN FUEL PROPERTIES AND 
COMBUSTION CARBON DEPOSITION. Edmund R. 
Jonash, Jerrold D. Wear and Robert R. Hibbard. 
April 1952. 67p. diagrs., 3 tabs. (NACA 
RM E52B14) 



TURBINE ENGINES, RAM JETS, 

AND PULSE JETS 

(3.4.3.2) 

COMPARISON OF PERFORMANCE OF AN-F-58 
AND AN-F-32 FUELS IN J33-A-23 TURBOJET 
ENGINE. H. D. Wilsted and J. C. Armstrong. 
June 2, 1949. 33p. photos., diagrs., tab. (NACA 
RM E8K24) 



PROPULSION 
FUEL (3.4) 



125 



Turbine Engines, Ram Jets, 
and Pulse Jets (Gont. ) 

CARBON DEPOSITION FROM AN-F-58 FUELS IN A 
J33 SINGJ^ COMBUSTOR. Jerrold D. Wear and 
Howard W. Douglass. June 24, 1949. 27p. diagrs., 
photos,, 2 tabs. (NACA RM E9D06) 

INVESTIGATION OF IGNITION CHARACTERISTICS 
OF AN-F-32 AND TWO AN-F-58a FUELS IN 
SINGLE CAN-TYPE TURBOJET COMBUSTOR. 
Warren D. Rayle and Howard W. Douglass. 
October 13, 1950. 25p. photos., diagrs., 2 tabs. 
(NACA RM E50H16a) 

COMBUSTION EFFICIENCY AND ALTITUDE OPER- 
ATIONAL LIMITS OF THREE LIQUID HYDRO- 
CARBON FUELS HAVING HIGH VOLUMETRIC 
ENERGY CONTENT IN A J33 SINGLE COMBUSTOR. 
Edward G. Strieker. November 6, 1950. 22p. 
diagrs., tab. (NACA RM E50H28) 

COMBUSTION PROPERTIES OF ALUMINUM AS 
RAM-JET FUEL. J. Robert Branstetter, Albert M. 
Lord and Melvin Gerstein. March 28, 1951. 37p. 
diagrs., photos. (NACA RM E51B02) 

CARBON DEPOSITION OF SEVERAL SPECIAL 
TURBOJET-ENGINE FUELS. Jerrold D. Wear and 
James W. Useller. April 10, 1951. 15p. photos., 
diagr., tab. (NACA RM E51C02) 



EFFECT OF FUEL VOLATILITY ON PERFORM- 
ANCE OF TAIL-PIPE BURNER. Zelmar Barson 
and Arthur F. Sargent, Jr. April 30, 1951. IBp. 
diagrs., tab. (NACA RM E51C14) 



RELATIONS BETWEEN FUEL PROPERTIES AND 
COMBUSTION CARBON DEPOSITION. Edmund R. 
Jonash, Jerrold D. Wear and Robert R. Hibbard. 
April 1952. 67p. diagrs., 3 tabs. (NACA 
RM E52B14) 

BURNING RATES OF SINGLE FUEL DROPS AND 
THEIR APPLICATION TO TURBOJET COMBUS- 
TION PROCESS. Charles C. Graves. July 1953. 
35p. diagrs., photos., tab. (NACA RM E53E22) 



ROCKETS (INCLUDES FUEL 

AND OXIDANT) 

(3.4.3,3) 



PHOTOGRAPHIC INVESTIGATION OF COMBUSTION 
IN A TWO-DIMENSIONAL TRANSPARENT ROCKET 
ENGINE. Donald R. Bellman, Jack C. Humphrey 
and Theodore Male. 1953. ii, 12p. diagrs., photos., 
tab. (NACA Rept. 1134. Formerly RM E8F01) 



CORROSION OF METALS OF CONSTRUCTION BY 
ALTERNATE EXPOSURE TO LIQUID AND 
GASEOUS FLUORINE. Richard M. Gundzik and 
Charles E. Feiler. December 1954. lOp. photos., 

3 tabs. (NACA TN 3333) 

IGNITION-DELAY DETERMINATIONS OF 
FURFURYL ALCOHOL AND MIXED BUTYL 
MERCAPTANS WITH VARIOUS WHITE FUMING 
NITRIC ACIDS USING MODIFIED OPEN-CUP AND 
SMALL-SCALE ROCKET ENGINE APPARATUS. 
Dezso J. Ladanyi, Riley O. Miller and Glen 
Hennings. February 1955. 17p. diagrs., photos., 

4 tabs. (NACA RM E53E29) 



126 PROPULSION 



Combustion and Combusfors 

(3.5) 



COMPARISON OF THEORETICALLY AND EXPERI- 
MENTALLY DETERMINED EFFECTS OF OXIDE 
COATINGS SUPPLIED BY FUEL ADDITIVES ON 
UNCOOLED TURBINE-BLADE TEMPERATURE 
DURING TRANSIENT TURBOJET-ENGINE OPERA- 
TION. Louis J. Schafer, Jr., Francis S. Stepka 
and W. Byron Brown. March 1953. 45p. photos., 
diagrs., tab. (NACA RM E53A19) 



GENERAL COMBUSTION 

RESEARCH 

(3.5.1) 



BURNING RATES OF SINGLE FUEL DROPS AND 
THEIR APPLICATION TO TURBOJET COMBUS- 
TION PROCESS. Charles C. Graves. July 1953. 
35p. diagrs., photos., tab. (NACA RM E53E22) 

PREDICTION OF FLAME VELOCITIES OF 
HYDROCARBON FLAMES. Gordon L. Dugger and 
Dorothy M. Simon. 1954. ii. lOp. diagrs., 4 tabs. 
(NACA Rept. 1158. Formerly RM E52J13) 

FORMATION AND COMBUSTION OF SMOKE IN 
LAMINAR FLAMES. Rose L. Schalla, Thomas P. 
Clark and Glen E. McDonald. 1954. ii, 21p. 
diagrs., photos. (NACA Rept. 1186. Formerly 
RM E51E15; RM E52G24; RM E52I22; RM E52I26; 
RM E53E05; RM E53J12; RM E54E03) 

BURNING TIMES OF MAGNESIUM RIBBONS IN 
VARIOUS ATMOSPHERES. Kenneth P. Coffin. 
December 1954. 37p. diagrs., photos. (NACA 
TN 3332) 

A THERMAL EQUATION FOR FLAME QUENCHING. 
A. E. Potter, Jr. and A. L. Berlad. February 1955. 
18p. diagrs, tab. (NACA TN 3398) 

TEMPERATURE-COMPOSITION LIMITS OF SPON- 
TANEOUS EXPLOSION FOR NINE ALKYLSILANES 
WITH AIR AT ATMOSPHERIC PRESSURE. Rose L. 
Schalla and Glen E. McDonald. February 1955. 
13p. diagrs. (NACA TN 3405) 

LAMINAR-FLOW COMBUSTION 
(3.5.1. 1) 

PREDICTION OF FLAME VELOCITrES OF 
HYDROCARBON FLAMES. Gordon L. Dugger and 
Dorothy M. Simon. 1954. U. lOp. diagrs., 4 tabs. 
(NACA Rept. 1158. Formerly RM E52J13) 

FORMATION AND COMBUSTION OF SMOKE IN 
LAMINAR FLAMES. Rose L. Schalla, Thomas P. 
Clark and Glen E. McDonald. 1954. il, 21p. 
diagrs., photos. (NACA Rept. 1186. Formerly 
RM E51E15; RM E52G24; RM E52I22s RM E52I26; 
RM E53E05; RM E53J12: RM E54E03) 

A STUDY OF THE RADIATION FROM LAMINAR 
AND TURBULENT OPEN PROPANE-AIR FLAMES 
AS A FUNCTION OF FLAME AREA, EQUIVALENCE 
RATIO, AND FUEL FLOW RATE. Thomas P. Clark 
and David A. Bittker. August 1954. 33p. diagrs., 
photos., 2 tabs. (NACA RM E54F29) 



BURNING TIMES OF MAGNESIUM RIBBONS IN 
VARIOUS ATMOSPHERES. Kenneth P. Coffin. 
December 1954. 37p. diagrs., photos. (NACA 
TN 3332) 

CHAIN BREAKING AND BRANCHING IN THE 
ACTIVE-PARTICLE DIFFUSION CONCEPT OF 
QUENCHING. Frank E. Belles and A. L. Berlad. 
February 1955. 37p. diagrs, 3 tabs. (NACA 
TN 3409) 



TURBULENT-FLOW COMBUSTION 
(3. 5.1.2) 

A PRELIMINARY INVESTIGATION OF COMBUSTION 
WITH ROTATING FLOW IN AN ANNULAR COM- 
BUSTION CHAMBER. Ira R'. Schwartz. September 
1951. 18p. diagrs., photos. (NACA RM L51E25a) 

A,3TUDY OF THE RADIATION FROM LAMINAR 
AND TURBULENT OPEN PROPANE-AIR FLAMES 
AS A FUNCTION OF FLAME AREA, EQUIVALENCE 
RATIO, AND FUEL FLOW RATE. Thomas P. Clark 
and David A. Bittker. August 1954. 33p. diagrs., 
photos., 2 tabs. (NACA RM E54F29) 



INTERACTION OF A FREE FLAME FRONT WITH A 
TURBULENCE FIELD. Maurice Tucker. March 1955. 
55p. diagrs., 2 tabs. (NACA TN 3407) 



EFFECTS OF FUEL ATOMIZATION 
(3.5.1.4) 



PHOTOGRAPHIC INVESTIGATION OF COMBUSTION 
IN A TWO-DIMENSIONAL TRANSPARENT ROCKET 
ENGINE. Donald R. Bellman, Jack C. Humphrey 
and Theodore Male. 1953. ii, 12p. diagrs., photos., 
tab. (NACA Rept. 1134. Formerly RM E8F01) 



REACTION MECHANISMS 
(3.5.1.5) 

BURNING RATES OF SINGLE FUEL DROPS AND 
THEIR APPLICATION TO TURBOJET COMBUS- 
TION PROCESS. Charles C. Graves. July 1953. 
35p. diagrs., photos., tab. (NACA RM E53E22) 

FORMATION AND COMBUSTION OF SMOKE IN 
LAMINAR FLAMES. Rose L. Schalla, Thomas P. 
Clark and Glen E. McDonald. 1954. ii, 21p. 
diagrs., photos. (NACA Rept. 1186. Formerly 
RM E51E15; RM E52G24; RM E52I22i RM E52I26; 
RM E53E05; RM E53J12; RM E54E03) 

A THERMAL EQUATION FOR FLAME QUENCHING. 
A. E. Potter, Jr. and A. L. Berlad. February 1955. 
18p. diagrs, tab. (NACA TN 3398) 

CHAIN BREAKING AND BRANCHING IN THE 
ACTIVE-PARTICLE DIFFUSION CONCEPT OF 
QUENCHING. Frank E. Belles and A. L. Berlad. 
February 1955. 37p. diagrs, 3 tabs. (NACA 
TN 3409) 



PROPULSION 
COMBUSTION (3. 5) 



127 



IGNITION OF GASES 
(3. 5.1.6) 

SPARK IGNITION OF FLOWING GASES. IV - 
THEORY OF IGNITION IN NONTURBULENT AND 
TURBULENT FLOW USING LONG-DURATION 
DISCHARGES. Clyde C. Swett, Jr. August 1954. 
29p. diagrs., 2 tabs. (NACA RM E54F29a) 

EFFECT OF AMMONIA ADDITION ON LIMITS OF 
FLAME PROPAGATION FOR ISOOCTANE-AIR 
MIXTURES AT REDUCED PRESSURES AND ELE- 
VATED TEMPERATURES. Cleveland O'Neal, Jr. 
April 1955. 32p. diagrs., 3 tabs. (NACA TN 3446) 



EFFECT OF ENGINE 

OPERATING CONDITIONS 

& COMBUSTION CHAMBER 



GEOMETRY 
(3.5.2) 



ALTITUDE PERFORMANCE OF AN-F-58 FUELS IN 
J33-A-21 SINGLE COMBUSTOR. Ralph T. Dittrich 
and Joseph L. Jackson. April 8, 1949. 23p. 
diagrs.. 2 tabs. (NACA RM E8L24) 

BURNING RATES OF SINGLE FUEL DROPS AND 
THEIR APPLICATION TO TURBOJET COMBUS- 
TION PROCESS. Charles C. Graves. July 1953. 
35p. diagrs., photos., tab. (NACA RM E53E22) 

TRANSVERSE OSCILLATIONS IN A CYLINDRICAL 
COMBUSTION CHAMBER. Franklin K. Moore and 
Stephen H. Maslen. October 1954. 25p. diagrs. 
(NACA TN 3152) 



TURBINE ENGINES 
(3.5.2.2) 



ALTITUDE PERFORMANCE OF AN-F-58 FUELS IN 
J33-A-21 SINGLE COMBUSTOR. Ralph T. Dittrich 
and Joseph L. Jackson. April 8, 1949. 23p. 
diagrs., 2 tabs. (NACA RM E8L24) 



CARBON DEPOSITION FROM AN-F-58 FUEI5 IN A 
J33 SINGJ^ COMBUSTOR. Jerrold D. Wear and 
Howard W. Douglass. June 24, 1949. 27p. diagrs., 
photos., 2 tabs. (NACA RM E9D06) 

INVESTIGATION OF IGNITION CHARACTERISTICS 
OF AN-F-32 AND TWO AN-F-58a FUELS IN 
SINGLE CAN-TYPE TURBOJET COMBUSTOR. 
Warren D. Ray le and Howard W. Douglass. 
October 13, 1950. 25p. photos., diagrs., 2 tabs. 
(NACA RM E50H16a) 

COMBUSTION EFFICIENCY AND ALTITUDE OPER- 
ATIONAL LIMITS OF THREE LIQUID HYDRO- 
CARBON FUELS HAVING HIGH VOLUMETRIC 
ENERGY CONTENT IN A J33 SINGLE COMBUSTOR. 
Edward G. Strieker. November 6, 1950. 22p. 
diagrs., tab. (NACA RM E50H28) 

A PRELIMINARY INVESTIGATION OF COMBUSTION 
WITH ROTATING FLOW IN AN ANNULAR COM- 
BUSTION CHAMBER. Ira R. Schwartz. September 
1951. 18p. diagrs., photos. (NACA RM L51E25a) 

RAM -JET ENGINES 
(3. 5. 2. 3) 

COMBUSTION PROPERTIES OF ALUMINUM AS 
RAM-JET FUEL. J. Robert Branstetter, Albert M. 
Lord and Melvin Gerstein. March 28, 1951. 37p. 
diagrs., photos. (NACA RM E51B02) 

A PRELIMINARY INVESTIGATION OF COMBUSTION 
WITH ROTATING FLOW IN AN ANNULAR COM- 
BUSTION CHAMBER. Ira R. Schwartz. September 
1951. 18p. diagrs., photos. (NACA RM L51E25a) 



ROCKET ENGINES 
(3.5.2.5) 

PHOTOGRAPHIC INVESTIGATION OF COMBUSTION 
IN A TWO-DIMENSIONAL TRANSPARENT ROCKET 
ENGINE. Donald R. Bellman, Jack C. Humphrey 
and Theodore Male. 1953. ii, 12p. diagrs., photos., 
tab. (NACA Rept. 1134. Formerly RM E8F01) 

IGNITION-DELAY DETERMINATIONS OF 
FURFURYL ALCOHOL AND MIXED BUTYL 
MERCAPTANS WITH VARIOUS WHITE FUMING 
NITRIC ACIDS USING MODIFIED OPEN-CUP AND 
SMALL-SCALE ROCKET ENGINE APPARATUS. 
Dezso J. Ladanyi, Riley O. Miller and Glen 
Hennings. February 1955. 17p. diagrs., photos., 
4 tabs. (NACA RM E53E29) 



128 PROPULSION 



Compression and Compressors 

(3.6) 



EFFECT OF INLET TEMPERATURE AND HUMID- 
ITY ON THRUST AUGMENTATION OF TURBOJET 
ENGINE BY COMPRESSOR-INLET INJECTION. 
Thomas B. Shillito and James L. Harp, Jr. July 3, 
1950. 46p. dlagrs., photos. (NACA RM E50D19) 

A SELF-EXCITED, ALTERNATING-CURRENT, 
CONSTANT -TEMPERATURE HOT-WIRE ANEMOM- 
ETER. Charles E. Shepard. April 1955. 29p. 
dlagrs., photos. (NACA TN 3406) 



FLOW THEORY AND 

EXPERIMENT 

(3.6.1) 



PREDICTION OF LOSSES INDUCED BY ANGLES OF 
ATTACK IN CASCADES OF SHARP-NOSED BLADES 
FOR INCOMPRESSIBLE AND SUBSONIC COMPRES- 
SIBLE FLOW. James J. Kramer and John D. 
Stanitz. January 1955. 45p. dlagrs. (NACA 
TN 3149) 

AXIAL FLOW 
(3.6. 1. 1) 

APPROXIMATE EFFECT OF LEADING-EDGE 
THICKNESS, INCIDENCE ANGLE, AND INLET 
MACH NUMBER ON INLET LOSSES FOR HIGH- 
SOLIDITY CASCADES OF LOW CAMBERED 
BLADES. Linwood C. Wright. December 1954. 
38p. dlagrs. (NACA TN 3327) 

SHOCKS IN HELICAL FLOWS THROUGH ANNULAR 
CASCADES OF STATOR BLADES. Robert 
Wasserman and Arthur W. Goldstein. December 
1954. 27p. diagrs. (NACA TN 3329) 



RADIAL FLOW 
(3.6. 1.2) 

A NOTE ON SECONDARY FLOW IN ROTATING 
RADIAL CHANNELS. James J. Kramer and John 
D. Stanitz. 1954. 11, 12p. diagrs. (NACA 
Rept. 1179. Formerly TN 3013) 



A RAPID APPROXIMATE METHOD FOR THE 
DESIGN OF HUB SHROUD PROFILES OF CENTRIF- 
UGAL IMPELLERS OF GIVEN BLADE SHAPE. 
Kenneth J. Smith and Joseph T. Hamrlck. March 
1955. 26p. diagrs., 3 tabs. (NACA TN 3399) 

MIXED FLOW 
(3.6.1.3) 

DESIGN AND PERFORMANCE OF EXPERIMENTAL 
AXIAL-DISCHARGE MIXED-FLOW COMPRESSOR, 
n - PERFORMANCE OF IMPELLER. Ward W. 
Wilcox. August 12, 1948. 21p. dlagrs., photo. 
(NACA RM E8F07) 

A RAPID APPROXIMATE METHOD FOR THE 
DESIGN OF HUB SHROUD PROFILES OF CENTRIF- 
UGAL IMPELLERS OF GIVEN BLADE SHAPE. 
Kenneth J. Smith and Joseph T. Hamrlck. March 
1955. 26p. dlagrs., 3 tabs. (NACA TN 3399) 



STRESS AND VIBRATION 
(3.6.2) 



LIFT AND MOMENT EQUATIONS FOR OSCILLAT- 
ING AIRFOILS IN AN INFINITE UNSTAGGERED 
CASCADE. Alexander Mendelson and Robert W. 
Carroll. October 1954. 46p. diagrs., 3 tabs. 
(NACA TN 3263) 

A SELF-EXCITED, ALTERNATING-CURRENT, 
CONSTANT -TEMPERATURE HOT-WIRE ANEMOM- 
ETER. Charles E. Shepard. April 1955. 29p. 
dlagrs., photos. (NACA TN 3406) 



MATCHING 
(3.6.3) 

METHODS FOR RAPID GRAPHICAL EVALUATION 
OF COOLED OH UNCOOLED TURBOJET AND 
TURBOPROP ENGINE OR COMPONENT PERFORM- 
ANCE (EFFECTS OF VARIABLE SPECIFIC HEAT 
INCLUDED). Jack B. Esgar and Robert R. Ziemer. 
January 1955. 45p. diagrs. (NACA TN 3335) 



PROPULSION 129 



Turbines 
(3.7) 



EXPERIMENTAL INVESTIGATION OF THE VIBRA- 
TION CHARACTERISTICS OF FOUR DESIGNS OF 
TURBINE BLADES AND OF THE EFFECT PRO- 
DUCED BY VARYING THE AXIAL SPACING 
BETWEEN NOZZLE BLADES AND TURBINE 
BLADES. W. C. Morgan and C. R. Morse. 
February 1952. 28p. diagrs., photos., tab. (NACA 
RM E51J25) 

PRELIMINARY INVESTIGATION OF THE HEAT- 
SHOCK RESISTANT PROPERTIES OF MOLYBDE- 
NUM DISILICIDE BLADES UNDER CENTRIFUGAL 
LOAD. Roger A. Long and John C. Freche. May 
1952. 15p. diagrs., photos., tab. (NACA 
RM E52A17) 

COMPARISON OF THEORETICALLY AND EXPERI- 
MENTALLY DETERMINED EFFECTS OF OXIDE 
COATINGS SUPPLIED BY FUEL ADDITIVES ON 
UNCOOLED TURBINE-BLADE TEMPERATURE 
DURING TRANSIENT TUHBOJET-ENGINE OPERA- 
TION. Louis J. Schafer, Jr., Francis S. Stepka 
and W. Byron Brown. March 1953. 45p. photos., 
diagrs., tab. (NACA RM E53A19) 



FLOW THEORY AND 

EXPERIMENT 

(3.7.1) 

PREDICTION OF LOSSES INDUCED BY ANGLES OF 
ATTACK IN CASCADES OF SHARP-NC^ED BLADES 
FOR INCOMPRESSIBLE AND SUBSONIC COMPRES- 
SIBLE FLOW. James J. Kramer and John D. 
Stanitz. January 1955. 45p. diagrs. (NACA 
TN 3149) 

AXIAL FLOW 
(3.7.1. 1) 



STUDY OF STRESS STATES IN GAS-TURBINE DISK 
AS DETERMINED FROM MEASURED OPERATING- 
TEMPERATURE DISTRIBUTIONS. J. Elmo Farmer, 
M. B. MlUenson and S. S. Manson. July 21, 1948. 
41p. diagrs., photos. (NACA RM E8C16) 

EXPERIMENTAL INVESTIGATION OF THE VIBRA- 
TION CHARACTERISTICS OF FOUR DESIGNS OF 
TURBINE BLADES AND OF THE EFFECT PRO- 
DUCED BY VARYING THE AXIAL SPACING 
BETWEEN NOZZLE BLADES AND TURBINE 
BLADES. W. C. Morgan and C. R. Morse. 
February 1952. 28p. diagrs., photos., tab. (NACA 
RM E51J25) 

SECONDARY FLOWS AND BOUNDARY-LAYER 
ACCUMULATIONS IN TURBINE NOZZLES. Harold 
E. Rohlik, Milton G. Kofskey, Hubert W. Allen and 
Howard Z. Herzig. 1954. 11, 32p. diagrs., photos., 
3 tabs. (NACA Rept. 1168. Formerly TN 2871; 
TN 2909; TN 2989) 

SMOKE STUDY OF NOZZLE SECONDARY FLOWS 
IN A LOW-SPEED TURBINE. Milton G. Kofskey 
and Hubert W. Allen. November 1954. 24p. diagrs. 
photos. (NACA TN 3260) 



APPROXIMATE EFFECT OF LEADING-EDGE 
THICKNESS, INCIDENCE ANGLE, AND INLET 
MACH NUMBER ON INLET LOSSES FOR HIGH- 
SOLIDITY CASCADES OF LOW CAMBERED 
BLADES. Linwood C. Wright. December 1954. 
38p. diagrs. (NACA TN 3327) 



RADIAL FLOW 
(3. 7. l.Z) 

A NOTE ON SECONDARY FLOW IN ROTATING 
RADIAL CHANNELS. James J. Kramer and John 
D. Stanitz. 1954. ii, 12p. diagrs. (NACA 
Rept. 1179. Formerly TN 3013) 



COOLING 
(3.7.2) 



STUDY OF STRESS STATES IN GAS-TURBINE DISK 
AS DETERMINED FROM MEASURED OPERATING- 
TEMPERATURE DBTRIBUTIONS. J. Elmo Farmer, 
M. B. MlUenson and S. S. Manson. July 21, 1948. 
41p. diagrs., photos. (NACA RM E8C16) 

EXPERIMENTAL INVESTIGATION OF AIR-FLOW 
UNIFORMITY AND PRESSURE LEVEL ON WIRE 
CLOTH FOR TRANSPIRATION-COOLING APPLICA- 
TIONS. Patrick L. Donoughe and Roy A. McKimion. 
July 1952. 28p. diagrs., photos., tab. (NACA 
RM E52E16) 

COMPARISON OF THEORETICALLY AND EXPERI- 
MENTALLY DETERMINED EFFECTS OF OXIDE 
COATINGS SUPPLIED BY FUEL ADDITIVES ON 
UNCOOLED TURBINE-BLADE TEMPERATURE 
DURING TRANSIENT TURBOJET -ENGINE OPERA- 
TION. Louis J. Schafer, Jr., Francis S. Stepka 
and W. Byron Brown. March 1953. 45p. photos,, 
diagrs., tab. (NACA RM E53A19) 

COMPARISON OF EFFECTIVENESS OF 
CONVECTION-, TRANSPIRATION-, AND FILM- 
COOLING METHODS WITH AIR AS COOLANT. 
E. R. G. Eckert and John N. B. Livingood. 1954. 
ii, 17p. diagrs. (NACA Rept. 1182. Formerly 
TN 3010) 

METHOD FOR RAPID DETERMINATION OF PRES- 
SURE CHANGE FOR ONE-DIMENSIONAL FLOW 
WITH HEAT TRANSFER, FRICTION, ROTATION, 
AND AREA CHANGE. James E. Hubbartt, Henry O. 
Slone and Vernon L. Arne. June 1954. 22p. diagrs., 
2 tabs. (NACA TN 3150) 

HEAT, MASS, AND MOMENTUM TRANSFER FOR 
FLOW OVER A FLAT PLATE WITH BLOWING OR 
SUCTION. H. S. Mickley, R. C. Ross, A. L. Squyers 
and V/. E. Stewart, Massachusetts Institute of 
Technology. July 1954. ii, 149p. diagrs., photos., 
9 tabs. (NACA TN 3208) 

EXACT SOLUTIONS OF LAMINAR-BOUNDARY- 
LAYER EQUATIONS WITH CONSTANT PROPERTY 
VALUES FOR POROUS WALL WITH VARIABLE 
TEMPERATURE. Patrick L. Donoughe and John N. 
B. Livingood. September 1954. 42p. diagrs., 2 
tabs. (NACA TN 3151) 



PROPULSION 
130 TURBINES (3.7) 



Cooling (Cont. ) 



METHODS FOR RAPID GRAPHICAL EVALUATION 
OF COOLED OR UNCOOLED TURBOJET AND 
TURBOPROP ENGINE OR COMPONENT PERFORM- 
ANCE (EFFECTS OF VARIABLE SPECIFIC HEAT 
INCLUDED). Jack B. Esgar and Robert R. Ziemer. 
January 1955. 45p. dlagrs. (NACA TN 3335) 

EXPERIMENTS ON TURBULENT FLOW THROUGH 
CHANNELS HAVING POROUS ROUGH SURFACES 
WITH OR WITHOUT AIR INJECTION. E. R. G. 
Eckert, Anthony J. Diaguila and Patrick L. 
Donoughe. February 1955. 45p. diagrs., photos., 
tab. (NACA TN 3339) 

ONE -DIMENSIONAL CALCULATION OF FLOW IN A 
ROTATING PASSAGE WITH EJECTION THROUGH A 
POROUS WALL. E. R. G. Eckert, John N. B. 
Livingood and Ernst I. Prasse. March 1955. 29p. 
diagrs., photo. (NACA TN 3408) 



STRESS AND VIBRATION 



(3.7.3) 



STUDY OF STRESS STATES IN GAS-TURBINE DISK 
AS DETERMINED FROM MEASURED OPERATING- 
TEMPERATURE DISTRIBUTIONS. J. Elmo Farmer, 
M. B. MlUenson and S. S. Manson. July 21, 1948. 
41p. diagrs., photos. (NACA RM E8C16) 

INVESTIGATION OF MECHANISMS OF BLADE 
FAILURE OF FORGED HASTELLOY B AND CAST 
STELLITE 21 TURBINE BLADES IN TURBOJET 
ENGINE. C. Yaker, C. F. Robards and F. B. 
Garrett. August 1951. 41p. diagrs., photos., 2 tabs. 
(NACA RM E51D16) 



EXPERIMENTAL INVESTIGATION OF THE VIBRA- 
TION CHARACTERISTICS OF FOUR DESIGNS OF 
TURBINE BLADES AND OF THE EFFECT PRO- 
DUCED BY VARYING THE AXIAL SPACING 
BETWEEN NOZZLE BLADES AND TURBINE 
BLADES. W. C. Morgan and C. R. Morse. 
February 1952. 28p. diagrs., photos., tab. (NACA 
RM E51J25) 

BEHAVIOR OF FORGED S-816 TURBINE BLADES 
IN STEADY-STATE OPERATION OF J33-9 TURBO- 
JET ENGINE WITH STRESS-RUPTURE AND 
METALLOGRAPHIC EVALUATIONS. F. B. Garrett, 
C. A. Gyorgak and J. W. Weeton. February 1953. 
29p. diagrs., photos., Stabs. (NACA RM E52L17) 

THE DESIGN OF BRITTLE -MATERIAL BLADE 
HOOTS BASED ON THEORY AND RUPTURE TESTS 
OF PLASTIC MODELS. Andre J. Meyer, Jr., 
Albert Kaufman and WiUiam C. Caywood. 
April 6, 1953. 45p. diagrs., photos., tab. (NACA 
RM E53C12) 



MATCHING 
(3.7.4) 



METHODS FOR RAPID GRAPHICAL EVALUATION 
OF COOLED OR UNCOOLED TURBOJET AND 
TURBOPROP ENGINE OR COMPONENT PERFORM- 
ANCE (EFFECTS OF VARIABLE SPECIFIC HEAT 
INCLUDED). Jack B. Esgar and Robert R. Ziemer. 
January 1955. 45p. diagrs. (NACA TN 3335) 



PROPULSION J 31 



Friction and Lubrication 



(3.8) 



BtmVEY OF LESS-INFLAMMABLE HYDBAXJLIC 
FLinOS FOR AIRCRAFT. Wray V. Drake and 
I. L. DreU. September 7, 1950. 64p. 14 tabs. 
(HACA RM E50F29) 

THEORY AND EXPERIMENT 
(3.8.1) 

ANALYTICAL DERIVATION AND EXPERIMENTAL 
EVALUATION OF SHORT -BEARING APPROXIMA- 
TION FOR FULL JOURNAL BEARINCffi. George B. 
DuBois and Fred W. Ocvirk, Cornell Univ. 1953. 
li, 32p. diagrs., photos., 4 tabs. (NACA Rept. 1157. 
Formerly TN 2808; TN 2809) 

COMPARISON OF PERFORMANCE OF EXPERI- 
MENTAL AND CONVENTIONAL CAGE DESIGNS 
AND MATERIALS FOR 75-MILLIMETER-BORE 
CYLINDRICAL ROLLER BEARINGS AT HIGH 
SPEEDS. William J. Anderson, E. Fred Macks and 
ZoUon N. Nemeth. 1954. 11, 15p. diagrs., 6 tabs. 
(NACA Rept. 1177. Formerly TN 3001; TN 3002) 

EFFECTS OF CHEMICALLY ACTIVE ADDITIVES 
ON BOUNDARY LUBRICATION OF STEEL BY 
SILICONES. S. F. Murray and Robert L. Johnson. 
August 1954. 24p. diagrs., photos., tab. (NACA 
TN 3257) 



FRICTION OF POSSIBLE SOLID LUBRICANTS 
WITH VARIOUS CRYSTAL STRUCTURES. Marshall 
B. Peterson and Robert L. Johnson. December 

1954. 32p. diagrs., photos., 2 tabs. (NACA 
TN 3334) 

BOUNDARY LUBRICATION OF STEEL WITH 
FLUORINE- AND CHLORINE -SUBSTITUTED 
METHANE AND ETHANE GASES. S. F. Murray, 
Robert L. Johnson and Max A. Swikert. February 

1955. 17p. photos., diagrs., 2 tabs. (NACA 
TN 3402) 

HYDRODYNAMIC THEORY 
(3.8.1.1) 

INVESTIGATION OF TEMPERATURE LIMITATION 
OF VARIOUS LUBRICANTS FOR HIGH- 
TEMPERATURE 20-MILLIMETER -BORE BALL 
BEARIN<K. Z. N. Nemeth and W. J. Anderson. 
January 1955. 31p. diagrs., photos., 2 tabs. 
(NACA TN 3337) 

CHEMISTRY OF LUBRICATION 
(3.8.1.2) 

EFFECTS OF CHEMICALLY ACTIVE ADDITIVES 
ON BOUNDARY LUBRICATION OF STEEL BY 
SILICONES. S. F. Murray and Robert L. Johnson. 
August 1954. 24p. diagrs., photos., tab. (NACA 
TN 3257) 

FRICTION OF POSSIBLE SOLID LUBRICANTS 
WITH VARIOUS CRYSTAL STRUCTURES. Marshall 
B. Peterson and Robert L. Johnson. December 
1954. 32p. diagrs., photos., 2 tabs. (NACA 
TN 3334) 



INVESTIGATION OF TEMPERATURE LIMITATION 
OF VARIOUS LUBRICANTS FOR HIGH- 
TEMPERATURE 20-MILLIMETER-BORE BALL 
BEARINGS. Z. N. Nemeth and W. J. Anderson. 
January 1955. 31p. diagrs., photos., 2 tabs. 
(NACA TN 3337) 

BOUNDARY LUBRICATION OF STEEL WITH 
FLUORINE- AND CHLORINE -SUBSTITUTED 
METHANE AND ETHANE GASES. S. F. Murray, 
Robert L. Johnson and Max A. Swikert. February 
1955. 17p. photos., diagrs., 2 tabs. (NACA 
TN 3402) 

FRICTION, WEAR, AND SURFACE DAMAGE OF 
METALS AS AFFECTED BY SOLID SURFACE 
FILMS. Edmond E. Bisson, Robert L. Johnson, 
Max A. Swikert and Douglas Godfrey. May 1955. 
60p. diagrs., photos., tab. (NACA TN 3444) 



SURFACE CONDITIONS 
(3,8.1.3) 



FRICTION, WEAR, AND SURFACE DAMAGE OF 
METALS AS AFFECTED BY SOLID SURFACE 
FILMS. Edmond E. Bisson, Robert L. Johnson, 
Max A. Swikert and Douglas Godfrey. May 1955. 
60p. diagrs., photos., tab. (NACA TN 3444) 



SLIDING CONTACT SURFACES 
(3.8.2) 



FRICTION, WEAR, AND SURFACE DAMAGE OF 
METALS AS AFFECTED BY SOLID SURFACE 
FILMS. Edmond E. Bisson, Robert L. Johnson, 
Max A. Swikert and Douglas Godfrey. May 1955. 
60p. diagrs., photos., tab. (NACA TN 3444) 



SLEEVE BEARINGS 
(3.8.2.1) 



ANALYTICAL DERIVATION AND EXPERIMENTAL 
EVALUATION OF SHORT-BEARING APPROXIMA- 
TION FOR FULL JOURNAL BEARINGS. George B. 
DuBois and Fred W. Ocvirk, Cornell Univ. 1953. 
ii, 32p. diagrs., photos., 4 tabs. (NACA Rept. 1157. 
Formerly TN 2808; TN 2809) 

FUNDAMENTAL STUDY OF EROSION CAUSED BY 
STEEP PRESSURE WAVES. B. G. Rightmire and 
J. M. Bonneville, Massachusetts Institute of 
Technology. June 1954. 30p. diagrs., photos., 
2 tabs. (NACA TN 3214) 

EXPERIMENTAL INVESTIGATION OF MISALINING 
COUPLES AND ECCENTRICITY AT ENI« OF MBA- 
LINED PLAIN BEARINGS. G. B. DuBois, F. W. 
Ocvirk and R. L. Wehe, Cornell University. 
February 1955. 81p. diagrs., photo., 3 tabs. (NACA 
TN 3352) 



PROPULSION 
132 FRICTION AND LUBRICATION (3.8) 



ROLLING CONTACT SURFACES 
(3.8.3) 

ANTIFRICTION BEARINGS 
(3.8.3.1) 



COMPARISON OF PERFORMANCE OF EXPERI- 
MENTAL AND CONVENTIONAL CAGE DESIGNS 
AND MATERIALS FOR 75 -MILLIMETER -BORE 
CYLINDRICAL ROLLER BEARINGS AT HIGH 
SPEEDS. William J. Anderson, E. Fred Macks and 
Zolton N. Nemeth. 19S4. 11. 15p. dlagrs., 6 tabs. 
(NACA Rept. 1177. Formerly TN 3001; TN 3002) 

INVESTIGATION OF TEMPERATURE LIMITATION 
OF VARIOUS LUBRICANTS FOR HIGH- 
TEMPEHATURE 20-MILLIMETER-BORE BALL 
BEARINGS. Z. N. Nemeth and W. J. Anderson. 
January 1955. 31p. diagrs., photos., 2 tabs. 
(NACA TN 3337) 

FRICTION, WEAR, AND SURFACE DAMAGE OF 
METALS AS AFFECTED BY SOLID SURFACE 
FILMS. Edmond E. Bisson, Robert L. Johnson, 
Max A. Swikert and Douglas Godfrey. May 1955. 
60p. dlagrs., photos., tab. (NACA TN 3444) 



SLIDING AND ROLLING 

CONTACT SURFACES 

(3.8.4) 

COMPARISON OF PERFORMANCE OF EXPERI- 
MENTAL AND CONVENTIONAL CAGE DESIGNS 
AND MATERIALS FOR 75-MILLIMETER-BORE 
CYLINDRICAL ROLLER BEARINGS AT HIGH 
SPEEDS. William J. Anderson, E. Fred Macks and 
Zolton N. Nemeth. 1954. 11, 15p. dlagrs., 6 tabs. 
(NACA Rept. 1177. Formerly TN 3001; TN 3002) 



INVESTIGATION OF TEMPERATURE LIMITATION 
OF VARIOUS LUBRICANTS FOR HIGH- 
TEMPERATURE 20-MILLIMETER-BORE BALL 
BEARINGS. Z. N. Nemeth and W. J. Anderson. 
January 1955. 31p. diagrs., photos., 2 tabs. 
(NACA TN 3337) 



LUBRICANTS 
(3.8.5) 



EFFECTS OF CHEMICALLY ACTIVE ADDITIVES 
ON BOUNDARY LUBRICATION OF STEEL BY 
SILICONES. S. F. Murray and Robert L. Johnson. 
August 1954. 24p. diagrs., photos., tab. (NACA 
f»3257) 

FRICTION OF POSSIBLE SOLID LUBRICANTS 
WITH VARIOUS CRYSTAL STRUCTURES. Marshall 
B. Peterson and Robert L. Johnson. December 

1954. 32p. diagrs., photos., 2 tabs. (NACA 
TN 3334) 

INVESTIGATION OF TEMPERATURE LIMITATION 
OF VARIOUS LUBRICANTS FOR HIGH- 
TEMPERATURE 20-MILLIMETER-BORE BALL 
BEARINGS. Z. N. Nemeth and W. J. Anderson. 
January 19S5. 31p. diagrs., photos., 2 tabs. 
(NACA TN 3337) 

BOUNDARY LUBRICATION OF STEEL WITH 
FLUORINE- AND CHLORINE -SUBSTITUTED 
METHANE AND ETHANE GASES. S. F. Murray, 
Robert L. Johnson and Max A. Swikert. February 

1955. 17p. photos., diagrs., 2 tabs. (NACA 
TN 3402) 



FRICTION, WEAR, AND SURFACE DAMAGE OF 
METALS AS AFFECTED BY SOLID SURFACE 
FILMS. Edmond E. Bisson, Robert L. Johnson, 
Max A. Swikert and Douglas Godfrey. May 1955. 
60p. diagrs., photos., tab. (NACA TN 3444) 



PROPULSION 133 



Heat Transfer 

(3.9) 



COMPAHISON OF THEORETICALLY AND EXPERI- 
MENTALLY DETERMINED EFFECTS OF OXIDE 
COATINGS SUPPLIED BY FUEL ADDITIVES ON 
UNCOOLED TUHBINE-BLADE TEMPERATURE 
DURING TRANSIENT TURBOJET-ENGINE OPERA- 
TION. Louis J. Schafer, Jr., Francis S. Stepka 
and W. Byron Brown. March 1953. 45p. photos., 
diagrs., tab. (NACA RM E53A19) 

SOME MEASUREMENTS OF BOILING BURN-OUT. 
Warren H. Lowdermilk and Walter F. Wetland. 
February 1955. 18p. diagrs., photo., 3 tabs. 
(NACA RM E54K10) 

SIMILAR SOLUTIONS FOR THE COMPRESSIBLE 
LAMINAR BOUNDARY LAYER WITH HEAT 
TRANSFER AND PRESSURE GRADIENT. Clarence 
B. Cohen and Eli Reshotko. February 1955. 67p. 
diagrs., 2 tabs. (NACA TN 3325) 

REVIEW OF EXPERIMENTAL INVESTIGATIONS OF 
LIQUID -METAL HEAT TRANSFER. Bernard 
Lubarsky and Samuel J. Kaufmann. March 1955. 
115p. diagrs., tab. (NACA TN 3336) 



THE COMPRESSIBLE LAMINAE BOUNDARY LAYER 
WITH HEAT TRANSFER AND ARBITRARY PRES- 
SURE GRADIENT. Clarence B. Cohen and Eli 
Reshotko. April 1955. 43p. diagrs., 2 tabs. (NACA 
TN 3326) 

A SELF -EXCITED, ALTERNATING-CURRENT, 
CONSTANT -TEMPERATURE HOT-WIRE ANEMOM- 
ETER. Charles E. Shepard. April 1955. 29p. 
diagrs., photos. (NACA TN 3406) 



THEORY AND EXPERIMENT 
(3.9.1) 



DYNAMIC RESPONSE OF TURBINE -BLADE 
TEMPERATURE TO EXHAUST -GAS TEMPERA- 
TURE FOR GAS-TURBINE ENGINES. Richard Hood 
and William E. Phillips, Jr. February 1952. 41p. 
photos., diagrs. (NACA RM E52A14) 

COMPARISON OF THEORETICALLY AND EXPERI- 
MENTALLY DETERMINED EFFECTS OF OXIDE 
COATINGS SUPPLIED BY FUEL ADDITIVES ON 
UNCOOLED TURBINE-BLADE TEMPERATURE 
DURING TRANSIENT TURBOJET-ENGINE OPERA- 
TION. Louis J. Schafer, Jr., Francis S. Stepka 
and W. Byron Brown. March 1953. 45p. photos., 
diagrs., tab. (NACA RM E53A19) 

COMPARISON OF EFFECTIVENESS OF 
CONVECTION-, TRANSPIRATION-, AND FILM- 
COOLING METHODS WITH AIR AS COOLANT. 
E. R. G. Eckert and John N. B. Livingood. 1954. 
il, 17p. diagrs. (NACA Rept. 1182. Formerly 
TN 3010) 

EXPERIMENTAL HEAT-TRANSFER AND FRICTION 
COEFFICIENTS FOR AIR FLOWING THROUGH 
STACKS OF PARALLEL FLAT PLATES. Eldon W. 
Sams and Walter F. Weiland, Jr. August 1954. 33p. 
diagrs., photo., tab. (NACA RM E54F11) 



EXACT SOLUTIONS OF LAMINAR-BOUNDARY- 
LAYER EQUATIONS WITH CONSTANT PROPERTY 
VALUES FOR POROUS WALL WITH VARIABLE 
TEMPERATURE. Patrick L. Donoughe and John N. 
B. Livingood. September 1954. 42p. diagrs., 2 
tabs. (NACA TN 3151) 

VAPORIZATION RATES AND DRAG COEFFICIENTS 
FOR ISOOCTANE SPRAYS IN TURBULENT AIR 
STREAMS. Robert D. Ingebo. October 1954. 39p. 
diagrs., photos., 3 tabs. (NACA TN 3265) 

HEAT TRANSFER BY FREE CONVECTION FROM 
HORIZONTAL CYLINDERS IN DIATOMIC GASES. 
(Warmeubergang bei breier Stromung am wagrechten 
Zylinder in zweiatomigen Gasen). R. Hermann. 
November 1954. 73p. diagrs., photos., 6 tabs. 
(NACA TM 1366. Trans, from VDI Forschimgsheft, 
No. 379, 1936) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF HEAT TRANSFER BY LAMINAR NATURAL 
CONVECTION BETWEEN PARALLEL PLATES. 
A. F. Lietzke. December 1954. 23p. diagrs. 
(NACA TN 3328) 

AN ANALYTICAL ESTIMATION OF THE EFFECT 
OF TRANSPIRATION COOLING ON THE HEAT- 
TRANSFER AND SKIN-FRICTION CHARACTER- 
ISTICS OF A COMPRESSIBLE TURBULENT 
BOUNDARY LAYER. Morris W. Rubesin. 
December 1954. 56p. diagrs. (NACA TN 3341) 



ANALYSrS OF LAMINAR FORCED-CONVECTION 
HEAT TRANSFER IN ENTRANCE REGION OF FLAT 
RECTANGULAR DUCTS. E. M. Sparrow. .T:nni;iry 
1955. 42p. diagrs. (NACA TN 3331) 



MEASURED EFFECTIVE THERMAL CONDUCTIVITY 
OF URANIUM OXIDE POWDER IN VARIOUS GASES 
AND GAS MIXTURES. J. S. Boegli and R. G. 
Deissler. March 1955. 20p. diagrs., tab. (NACA 
RM E54L10) 

REVIEW OF EXPERIMENTAL INVESTIGATIONS OF 
LIQUID -METAL HEAT TRANSFER. Bernard 
Lubarsky and Samuel J. Kaufmann. March 1955. 
115p. diagrs., tab. (NACA TN 3336) 

A THEORY FOR PREDICTING THE FLOW OF REAL 
GASES IN SHOCK TUBES WITH EXPERIMENTAL 
VERIFICATION. Robert L. Trimpi and Nathaniel B. 
Cohen. March 1955. 69p. diagrs., photo. 
(NACA TN 3375) 

ONE-DIMENSIONAL CALCULATION OF FLOW IN A 
ROTATING PASSAGE WITH EJECTION THROUGH A 
POROUS WALL. E. R. G. Eckert, John N. B. 
Livingood and Ernst I. Prasse. March 1955. 29p. 
diagrs., photo. (NACA TN 3408) 



ANALYSIS OF FULLY DEVELOPED TURBULENT 
HEAT TRANSFER AND FLOW IN AN ANNULUS 
WITH VARIOUS ECCENTRICITIES. Robert G. 
Deissler and Maynard F. Taylor. May 1955. 42p. 
diagrs. (NACA TN 3451) 



PROPULSION 
134 HEAT TRANSFER (3. 9) 



HEAT EXCHANGERS 
(3.9.2) 

ANALYSIS OF LAMINAR FORCED-CONVECTION 
HEAT TRANSFER IN ENTRANCE REGION OF FLAT 
RECTANGULAR DUCTS. E. M. Sparrow. January 
1955. 42p. diagrs. (NACA TN 3331) 



ANALYSIS OF FULLY DEVELOPED TURBULENT 
BEAT TRANSFER AND FLOW DJ AN ANNULUS 
WITH VARIOUS ECCENTRICITIES. Robert G. 
Delsslier and Haynard F. Taylor. May 19S5. 4^. 
diagrs. (NACATN34S1) 



PROPULSION 135 



Cooling of Engines 
(3.10) 



EXPERIMENTAL INVESTIGATION OF AIR-FLOW 
tJNIFOHMITY AND PRESSURE LEVEL ON WIRE 
CLOTH FOR TRANSPIRATION-COOLING APPLICA- 
TIONS. Patrick L. Donoug^e and Hoy A. McKinnon. 
July 1952. 28p. dlagrs., photos., tab. (NACA 
RM E52£i6) 



GAS-TURBINE SYSTEMS 
(3.10.2) 



EXPERIMENTAL INVESTIGATION OF AIR-FLOW 
UNIFORMITY AND PRESSURE LEVEL ON WIRE 
CLOTH FOR TRANSPIRATION-COOLING APPLICA- 
TIONS. Patrick L. Donoughe and Roy A. McKinnon. 
July 1952. 28p. dlagrs., photos., tab. (NACA 
RM E52E16) 

COMPARISON OF EFFECTIVENESS OF 
CONVECTION-, TRANSPIRATION-, AND FILM- 
COOLING METHODS WITH AIR AS COOLANT. 
E. R. G. Eckert and John N. B. Livlngood. 1954. 
ii, 17p. dlagrs. (NACA Rept. 1182. Formerly 
TN 3010) 



EXPERIMENTS ON TURBULENT FLOW THROUGH 
CHANNELS HAVING POROUS ROUGH SURFACES 
WITH OR WITHOUT AIR INJECTION. E. R. G. 
Eckert, Anthony J. Diaguila and Patrick L. 
Donou^e. February 1955. 45p. diagrs., photos., 
tab. (NACA TN 3339) 

ANALYTICAL DETERMINATION OF EFFECT OF 
WATER INJECTION ON POWER OUTPUT OF 
TURBINE-PROPELLER ENGINE. Albert O. Ross 
and Merle C. Huppert. Bilarch 1955. 29p. diagrs. 
(NACA TN 3403. Formerly RM E9H17) 



RAM JETS 
(3.10.3) 



EXPERIMENTAL IN/ESTIGATION OF AIR-FLOW 
UNIFORMITY AND PRESSURE LEVEL ON WIRE 
CLOTH FOR TRANSPIRATION-COOLING APPLICA- 
TIONS. Patrick L. Donoughe and Roy A. McKinnon. 
July 1952. 28p. dlagrs., photos., tab. (NACA 
RM ES2E16) 



136 PROPULSION 



Properties of Gases 
(3.11) 



DETERMINATION OF VISCOSITY OF EXHAUST- 
GAS MIXTURES AT ELEVATED TEMPERATURES. 
J. C. Westmoreland, National Bureau of Standards. 
June 1954. 41p. diagrs., photo., 10 tabs. (NACA 
TN 3180) 



KINETIC 
(3.11.1) 

KINETIC TREATMENT OF THE NUCLEATION IN 
SUPERSATURATED VAPORS. (Kinetische 
Behandlung der Keimbildung in ubersattigten 
Dampfen). R. Becker and W. Dbrlng. September 
1954. 43p. diagrs. (NACA TM 1374. Trans, from 
Annalen der Physik, Ser. 5, v. 24, 1935, p. 719-752). 



THERMODYNAMIC 
(3.11.2) 



KINETIC TREATMENT OF THE NUCLEATION IN 
SUPERSATURATED VAPORS. (Kinetische 
Behandlung der Keimbildung in ubersattigten 
Dampfen). R. Becker and W. Doring. September 
1954. 43p. diagrs. (NACA TM 1374. Trans, from 
Annalen der Physik, Ser. 5, v. 24, 1935, p. 719-752). 



EFFECT OF DQSOCIATIOH ON THEHMODYNAMIC 
PROPERTIES OF PURE DIATOMIC GASES. Harold 
W. WooUey, National Bureau of Standards. April 
1955. 19p. diagra., tab. (NACA TN 3270) 



PROPULSION 137 



Accessories and Accessory Functions 

(3.12) 



FUEL SYSTEMS 
(3.12.1) 



AN EVALUATION OF NON-NEWTONIAN FLOW IN 
PIPE LINES. Ruth N. Weltmann. Febriiary 1955. 
40p. diagrs., tab. (NACATN3397) 



DESIGN AND PERFOHMANCE OF THROTTLE- 
TYPE FUEL CONTROLS FOR ENGINE DYNAMIC 
STUDIES. Edward W. Otto, Harold Gold and Kirby 
W. Hiller. April 1955. 39p. diagrs., photo. 
(NACA TN 3445) 



ROCKET ENGINES 
(3.12. 1.8) 



IGNITION-DELAY DETERMINATIONS OF 
FURFURYL ALCOHOL AND MIXED BUTYL 
MERCAPTANS WITH VARIOUS WHITE FUMING 
NITRIC ACIDS USING MODIFIED OPEN-CUP AND 
SMALL-SCALE ROCKET ENGINE APPARATUS. 
Dezso J. Ladanyi, Riley O. Miller and Glen 
Hennings. February 1955. 17p. diagrs., photos., 
4 tabs. (NACA RM E53E29) 



IGNITION SYSTEMS 
(3.12.2) 



ALTITUDE-IGNITION LIMIT OF A TURBOJET 
ENGINE USING A CONDENSER -DISCHARGE 
IGNITION SYSTEM. John C. Armstrong. October 
1951. 5p. diagrs. (NACA RM E51F11) 

SPARK IGNITION OF FLOWING GASES. IV - 
THEORY OF IGNITION IN NONTURBULENT AND 
TURBULENT FLOW USING LONG-DURATION 
DISCHARGES. Clyde C. Swett, Jr. August 1954. 
29p. diagrs., 2 tabs. (NACA RM E54F29a) 



COOLING SYSTEMS 
(3.12.5) 



SOME MEASUREMENTS OF BOILING BURN-OUT. 
Warren H. Lowdermllk and Walter F. Wetland. 
February 1955. 18p. diagrs., photo., 3 tabs. 
(NACA RM E54K10) 



138 PROPULSION 



Vibration and Flutter 
{3.13) 



TRANSVERSE OSCILLATIONS IN A CYLINDRICAL 
COMBUSTION CHAMBER. Franklin K. Moore and 
Stephen H. Maslen. October 1954. 25p. dlagrs. 
(NACA TN 3152) 



THE EFFECTS OF VARIOUS PAHAMETEHS, 
INCLUDING MACE NUMBER, ON PROPELLER- 
BLADE FLUTTER WITH EMPHASIS ON STALL 
FLUTTER. John E. Baker. January 1955. 40p. 
diagrs., 3 Ubs. (NACA TN 3357. Formerly 
RM L50L12b) 




AIRCRAFT LOADS 
AND CONSTRUCTION 

(4) 



LOADS AND CONSTRUCTION 139 



AIRCRAFT LOADS 
and CONSTRUCTION 

(4) 



AN EXPERIMENTAL INVESTIGATION OF WHEEL 
SPIN-UP DRAG LOADS. Benjamin Milwitzky, Dean 
C. Lindquist and Dexter M. Potter. September 1954. 
18p. diagrs. (NACA TN 3246. Formerly 
RM L53E06b) 



140 



LOADS AND CONSTRUCTION 



Loads 
(4.1) 



AN EXPERIMENTAL INVESTIGATION OF WHEEL 
SPIN-UP DRAG LOADS. Benjamin Milwitzky, Dean 
C. Lindqulst and Dexter M. Potter. September 1954. 
18p. dlagrs. (NACA TN 3246. Formerly 
RM L53E06b) 



AERODYNAMIC 
(4.1.1) 



FLIGHT DETERMINATION OF THE EFFECTS OF 
WING VORTEX GENERATORS ON THE AERO- 
DYNAMIC CHARACTERISTICS OF THE DOUGLAS 
D-558-I AIRPLANE. De E. Beeler, Donald R. 
Bellman and John H. Griffith. August 14, 1951. 23p. 
dlagrs., photos., tab. (NACA RM L51A23) 

AERODYNAMIC CHARACTERISTICS OF A 
LEADING-EDGE SLAT ON A 35° SWEPT -BACK 
WING FOR MACH NUMBERS FROM 0.30 TO 0.88. 
John A. Kelly and Nora-Lee F. Hayter. December 
1951. 49p. diagrs., tab. (NACA RM A51H23) 

PRESSURE PULSATIONS ON RIGID AIRFOILS AT 
TRANSONIC SPEEDS. Milton D. Humphreys. 
December 1951. 21p. diagrs., photos., tab. 
(NACA RML5 1112) 

AN APPLICATION OF THE ROCKET-PROPELLED- 
MODEL TECHNIQUE TO THE INVESTIGATION OF 
LOW-LIFT BUFFETING AND THE RESULTS OF 
PRELIMINABY TESTS. Homer P. Mason and 
William N. Gardner. September 1952. 19p. 
diagrs., photos. (NACA RM L52C27) 

THE EFFECTS OF CAMBER AND LEADING-EDGE - 
FLAP DEFLECTION ON THE PRESSURE PULSA- 
TIONS ON THIN RlOro AIRFOILS AT TRANSONIC 
SPEEDS. Milton D. Humphreys and John D. Kent- 
October 1952. 26p. diagrs., photos., tab. (NACA 
RM L52G22) 

TRANSONIC AERODYNAMIC CHARACTERISTICS 
OF AN NACA 64A006 AIRFOIL SECTION WITH A 
15-PERCENT -CHORD LEADING-EDGE FLAP. 
Milton D. Humphreys. September 1953. 44p. 
diagrs., photos. (NACA RM L53G23) 

AERODYNAMIC LOADS ON A LEADING-EDGE 
FLAP AND A LEADING-EDGE SLAT ON THE 
NACA 64A010 AIRFOIL SECTION. John A. Kelly 
and George B. McCuUough. June 1954. 33p. 
diagrs., 8 tabs. (NACA TN 3220) 

AN INVESTIGATION OF A LIFTING 10-PERC?NT- 
THICK SYMMETRICAL DOUBLE-WEDGE AIRFOIL 
AT MACH NUMBERS UP TO 1. Milton D. 
Humphreys. November 1954. 35p. diagrs., photos., 
tab. (NACA TN 3306) 



WINGS 
(4.1.1.1) 



EXPERIMENTAL PRESSURE DISTRIBUTIONS OVER 
WING TIPS AT MACH NUMBER 1.9. I - WING TIP 
WITH SUBSONIC LEADING EDGE. James M. 
Jagger and Harold Mirels. January 27, 1949. 28p. 
dlagrs., photo. (NACA RM E8K26) 

ESTIMATION OF LIFT AND DRAG OF AIRFOILS AT 
NEAR SONIC SPEEDS AND IN THE PRESENCE OF 
DETACHED SHOCK WAVES. John P. Mayer. 
February 23, 1949. 23p. dlagrs. (NACA RM L8L07) 

AN ANALYSIS OF AVAILABLE DATA ON EFFECTS 
OF WING-FUSELAGE-TAIL AND WING-NACELLE 
INTERFERENCE ON THE DISTRIBUTION OF THE 
AIR LOAD AMONG COMPONENTS OF AIRPLANES. 
Bertram C. WoUner. April 11, 1949. 33p. diagrs., 
tab. (NACA RM L9B10) 

TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED IN 
FLIGHT ON THE WING OF THE DOUGLAS D-558-I 
AIRPLANE FOR A 1 g STALL, A SPEED RUN TO A 
MACH NUMBER OF 0.90, AND A WIND-UP TURN 
AT A MACH NUMBER OF 0.86. Earl R. Keener and 
Mary Pierce. December 15, 1950. 40p. diagrs., 
photos., 5 tabs. (NACA RM L50J10) 

UFT AND MOMENT CHARACTERBTICS AT SUB- 
SONIC MACH NUMBERS OF FOUR IQ-PERCENT- 
THICK AIRFOIL SECTIONS OF VARYING TRAILDJG- 
EDGE THICKNESS. James L. Summers and William 
A. Page. December 20, 1950. 32p. diagrs., photos. 
(NACA RM A50J09) 

TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED 
IN FLIGHT ON THE WING OF THE DOUGLAS 
D-558-I AIRPLANE THROUGHOUT THE NORMAL- 
FORCE-COEFFICIE>rT RANGE AT MACH NUMBERS 
OF 0.67, 0.74, 0.78, AND 0.82. Earl R. Keener, 
James R. Peele and Julia B. Woodbridge. 
January 29, 1951. 37p. diagrs., photos., 6 tabs. 
(NACA RM L50L12a) 

PRESSURE-DISTRIBUTION MEASUREMENTS OVER 
A 45° SWEPTBACK WING AT TRANSONIC SPEEDS 
BY THE NACA WING-FLOW METHOD. Edward 
C. B. Danforth and Thomas C. O'Bryan. June 1951. 
42p. diagrs., photos. (NACA RM L51D24) 

TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED IN 
FLIGHT ON THE WING OF THE D-558-I RESEARCH 
AIRPLANE THROUGH A MACH NUMBER RANGE 
OF 0.80 TO 0.89 AND THROUGHOUT THE 
NORMAL-FORCE-COEFFICIENT RANGE AT MACH 
NUMBERS OF 0.61, 0.70, 0.855, AND 0.88. Earl 
R. Keener and Rozalia M. Bandish. August 1951. 
43p. diagrs., photos., 7 tabs. (NACA RM L51F12) 

A METHOD FOR THE DESIGN OF SWEPTBACK 
WINGS WARPED TO PRODUCE SPECIFIED FLIGHT 
CHARACTERISTICS AT SUPERSONIC SPEEDS. 
Warren A. Tucker. September 1951. 52p. diagrs., 
2 tabs. (NACA RM L51F08) 



LOADS AND CONSTRUCTION 
LOADS (4. 1) 



141 



Wings - Aerodynamic (Cont. ) 

LOAD DISTRIBUTION OVER A FUSELAGE IN COM- 
BINATION WITH A SWEPT WING AT SMALL 
ANGLES OF ATTACK AND TRANSONIC SPEEDS. 
Maurice D. White and Bonne C. Look. November 

1951. 26p. diagrs., photo., tab. (NACA RM 
A51H15) 

THE INTERFERENCE EFFECTS OF A BODY ON 
THE SPANWISE LOAD DISTRIBUTIONS OF TWO 
45° SWEPTBACK WINGS OF ASPECT RATIO 8 
FROM LOW-SPEED TESTS AT A REYNOLDS 
NUMBER OF 4 X lO^. Albert P. Martina. February 

1952. 48p. diagrs., photo., 2 tabs. (NACA 
RM L51K23) 

WING AND FUSELAGE LOADS MEASURED IN 
FLIGHT ON THE NORTH AMERICAN B-45 AND 
F-82 AIRPLANES. Paul W. Harper. February 

1953. 35p. diagrs., 4 tabs. (NACA RM L52L09) 

OSCILLATING PRESSURES NEAR A STATIC 
PUSHER PROPELLER AT TIP MACH NUMBERS UP 
TO 1.20 WITH SPECIAL REFERENCE TO THE EF- 
FECTS OF THE PRESENCE OF THE WING. Harvey 
H. Hubbard and Leslie W. Lassiter. July 1954. 
35p. diagrs., photos., tab. (NACA TN 3202) 

ON THE KERNEL FUNCTION OF THE INTEGRAL 
EQUATION RELATING LIFT AND DOWNWASH DIS- 
TRIBUTIONS OF OSCILLATING WINGS IN SUPER- 
SONIC FLOW. Charles E. Watkins and Julian H. 
Herman. May 1955. 43p. (NACA TN 3438) 



Steady Loads 
(4.1.1.1.1) 



MEASUREMENTS OF THE WING AND TAIL LOADS 
DURING THE ACCEPTANCE TESTS OF BELL 3B-1 
RESEARCH AIRPLANE. De E. Beeler and John P. 
Mayer. April 13, 1948. 25p. diagrs., photos., 2 
tabs. (NACA RM L7L12) 

INVESTIGATION AT SUPERSONIC SPEED (M = 1. 53) 
OF THE PRESSURE DISTRIBUTION OVER A 63° 
SWEPT AIRFOIL OF BICONVEX SECTION AT 
ZERO LIFT. Charles W. Frick and John W. Boyd. 
June 10, 1948. 33p. diagrs., photos. (NACA 
RM A8C22) 

INVESTIGATION AT SUPHISONIC SPEED (M = 1.53) 
OF THE PRESSURE DISTRIBUTION OVER A 63° 
SWEPT AIRFOIL OF BICONVEX SECTION AT SEV- 
ERAL ANGLES OF ATTACK. John W. Boyd, Elliott 
O. Katzen and Charles W. Frick. September 24, 

1948. 41p. diagrs., photos., tab. (NACA RM A8F22) 

PRESSURE-DISTRIBUTION DATA FOR THE NACA 
641-012 AND 641A012 AIRFOILS AT HIGH SUBSONIC 
MACH NUMBERS. Milton D. Humphreys. May 6, 

1949. 37p. photos. , diagrs. , 8 tabs. (NACA 
RM L9C18) 

EXPERIMENTAL PRESSURE DISTRIBUTIONS OVER 
WING TIPS AT MACH NUMBER 1.9. H - WING TIP 
WITH SUBSONIC TRAILING EDGE. Harold Mirels 
and James M. Jagger. December 21, 1949. 23p. 
diagrs., photo. (NACA RM E9I22a) 

INVESTIGATION AT MACH NUMBER 1.62 OF THE 
PRESSURE DISTRIBUTION OVER A RECTANGULAR 
WING WITH SYMMETRICAL CIRCULAK-ARC SEC- 
TION AND 30-PERCENT -CHORD TRAILING-EDGE 
FLAP. K. R. Czarnecki and James N. Mueller. 
January 25, 1950. 81p. diagrs., photos. (NACA 
RM L9J05) 



INVESTIGATION AT HlCai SUBSONIC SPEEDS OF 
METHODS OF ALLEVIATING THE ADVERSE 
INTERFERENCE AT THE ROOT OF A SWEPT- 
BACK WING. LeeE. Boddy. Ai^ust 10, 1950. 31p. 
diagrs., photos. (NACA RM A50E26) 

PRESSURE DISTRIBUTIONS OVER A RETRACTED 
LEADING-EDGE SLAT ON A 40° SWEPTBACK WING 
AT MACH NUMBERS UP TO 0.9. Jones F. Cahill 
and Gale C. Oberndorfer. January 26, 1951. 36p. 
diagrs. (NACA RM L50L04a) 

PRESSURE DISTRIBUTION AT LOW SPEED ON A 
1/4-SCALE BELL X-5 AIRPLANE MODEL. 
William B. Kemp, Jr. and Albert G. Few, Jr. 
December 1951. 86p. diagrs., photos. (NACA 
RM L51I25) 

THE CALCULATION OF CERTAIN STATIC AERO- 
ELASTIC PHENOMENA OF WINGS WITH TIP 
TANKS OR BOOM-MOUNTED LIFTING SURFACES. 
Franklin W. Dlederich and Kenneth A. Fobs. 
August 1952. 55p. diagrs., 2 tabs. (NACA 
RM L52A22) 

AERODYNAMIC FORCES AND LOADINGS ON 
SYMMETRICAL CIRCULAR -ARC AIRFOILS WITH 
PLAIN LEADING-EDGE AND PLAIN TRAILING- 
EDGE FLAPS. Jones F. CahiU, William J. 
Underwood, Robert J. Nuber and Gail A. Cheesman. 
1953. ii, 38p. diagrs,, photos., 5 tabs. (NACA Rept. 
1146. Formerly RML6K22; RML7H04; RML50H17a) 

SOME NOTES ON THE AERODYNAMIC LOADS 
ASSOCIATED WITH EXTERNAL-STORE 
INSTALLATIONS. H. Norman Silvers and Thomas 
C. O'Bryan. June 1953. 17p. diagrs. (NACA 
RM L53E06a) 



Maneuvering 
(4.1.1.1.2) 



MEASUREMENTS OF THE WING AND TAIL LOADS 
DURING THE ACCEPTANCE TESTS OF BELL XS-1 
RESEARCH AIRPLANE. De E. Beeler and John P. 
Mayer. April 13, 1948. 25p. diagrs., photos., 2 
tabs. (NACA RM L7L12) 

A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT -WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
Seth B. Anderson and Richard S. Bray. November 
1951. 33p. diagrs., photo., tab. (NACA RM A51I12) 

WING AND FUSELAGE LOADS MEASURED IN 
FLIGHT ON THE NORTH AMERICAN B-45 AND 
F-82 AIRPLANES. Paul W. Harper. February 
1953. 35p. diagrs., 4 tabs. (NACA RM L52L09) 

MATRIX METHODS FOB DETERMINING THE 
LONGITUDMAL-STABILnT DERIVATIVES OF AN 
AIRPLANE FROM TRANSIENT FLIGHT DATA. 
James J. Donegan. 1954. ii, 20p. diagrs., 6 tabs. 
(NACA Rept. 1169. Formerly TN 2902) 

THEORETICAL ANALYSIS OF AN AIRPLANE 
ACCELERATION RESTRICTOR CONTROLLED BY 
NORMAL ACCELERATION, PITCHING ACCELERA- 
TION, AND PITCHING VELOCITY. Christopher C. 
Kraft, Jr. September 1954. 42p. diagrs., 3 tabs. 
(NACA TN 3243) 

GENERALIZED INDICIAL FORCES ON DEFORMING 
RECTANGULAR WINGS IN SUPERSONIC FLIGHT. 
Harvard Lomax, Franklyn B. Fuller and Loma Sluder. 
November 1954. 74p. diagrs., tab. (NACA TN 3286) 



LOADS AND CONSTRUCTION 
142 LOADS (4.1) 



Maneuvering - Aerodynamic 
(Cont. ) 



OPERATING CHARACTERISTICS OF AN 
ACCELERATION RESTRICTOR AS DETERMINED 
BY MEANS OF A SIMULATOR. Arthur 
Assadourian. December 1954. 20p. diagrs., 
photos. (NACATN3319) 

SOME CONSIDERATIONS ON TWO-DIMENSIONAL 
ram AIRFOILS DEFORMING IN SUPERSONIC 
FLOW. Eugene Migots^. January 1955. 36p. 
diagrs. (NACA TN 3386) 

AN ANALYSIS OF ACCELERATIONS, AIRSPEEDS, 
AND GUST VELOCITIES FROM THREE COMMER- 
CIAL OPERATIONS OF ONE TYPE OF MEDIUM - 
ALTITUDE TRANSPORT AIRPLANE. Thomas L. 
Coleman, Martin R. Copp, Walter G. Walker and 
Jerome N. Engel. March 1935. 31p. diagrs., 
4 tabs. (NACA TN 3365) 



Gust Loads 



(4.1.1.1.3) 



A COMPARISON OF GUST LOADS MEASURED IN 
FLIGHT ON A SWEPT -WING AIRPLANE AND AN 
UNSWEPT-WING AIRPLANE. Jack Funk and 
Harry C. Mickleboro. June 1953. 16p. diagrs., 
2 tabs. (NACA RM L52L02) 

LIFT DEVELOPED ON UNRESTRAINED RECTAN- 
GULAR WINGS ENTERING GUSTS AT SUBSONIC 
AND SUPERSONIC SPEEDS. Harvard Lomax. 1954. 
ii, 16p. diagrs., 5 tabs. (NACA Rept. 1162. 
Formerly TN 2925) 

A STUDY OF THE APPLICATION OF POWER- 
SPECTRAL METHODS OF GENERAUZED HARMON- 
IC ANALYSIS TO GUST LOADS ON AIRPLANES. 
Harry Press and Bernard Mazelsky. 1954. ii, 17p. 
diagrs., 2 tabs. (NACA Rept. 1172. Formerly 
TN 2853) 

AN INVESTIGATION OF THE USE OF ROCKET- 
POWERED MODELS FOR GUST-LOAD STUDIES 
WITH AN APPLICATION TO A TAILLESS SWEPT- 
■WEJG MODEL AT TRANSONIC SPEEDS. A. James 
Vitale, H. Press and C. C. Shufflebarger. June 
1954. 36p. diagrs., photos., tab. (NACA TN 3161) 

SOME MEASUREMENTS OF ATMOSPHERIC 
TURBULENCE OBTAINED FROM FLOW-DIRECTION 
VANES MOUNTED ON AN AIRPLANE. Robert G. 
Chilton. November 1954. 22p. diagrs., photo., 
tab. (NACA TN 3313) 

GUST EXPERIENCE OF A HELICOPTER AND AN 
AIRPLANE IN FORMATION FLIGHT. Aimer D. 
Crim. December 1954. 12p. diagrs., photos., 
2 Ubs. (NACA TN 3354) 

GUST -LOAD AND AIRSPEED DATA FROM ONE 
TYPE OF FOUR-ENGINE AIRPLANE ON FIVE 
ROUTES FROM 1947 TO 1954. Walter G. Walker. 
January 1955. 28p. diagrs., 4 tabs. (NACA 
TN 3358) 

ANALYSIS OF ACCELERATIONS, GUST VELOCI- 
TIES, AND AIRSPEEDS FROM OPERATIONS OF A 
TWIN-ENGINE TRANSPORT AIRPLANE ON A 
TRANSCONTINENTAL ROUTE FROM 1950 TO 1952. 
Thomas L. Coleman and Walter G. Walker. 
February 1955. 16p. diagrs., 3 tabs. (NACA 
TN 3371) 



ESTIMATES OF PROBABILITY DISTRIBUTION OF 
ROOT -MEAN-SQUARE GUST VELOCITY OF 
ATMOSPHERIC TURBULENCE FROM OPERATION- 
AL GUST -LOAD DATA BY RANDOM -PROCESS 
THEORY. Harry Press, May T. Meadows and Ivan 
Hadlock. March 1955. 48p. diagrs., 4 tabs. 
(NACA TN 3362) 

AN ANALYSIS OF ACCELERATIONS, AIRSPEEDS, 
AND GUST VELOCITIES FROM TtoEE COMMER- 
CTAL OPERATIONS OF ONE TYPE OF MEDIUM- 
ALTITUDE TRANSPORT AIRPLANE. Thomas L. 
Coleman, Martin R. Copp, Walter G. Walker and 
Jerome N. Engel. March 1955. 31p. diagrs., 
4 tabs. (NACA TN 3365) 



TAIL 

(4.1.1.2) 

AN ANALYSIS OF AVAILABLE DATA ON EFFECTS 
OF WING-FUSELAGE-TAIL AND WING-NACELLE 
INTERFERENCE ON THE DISTRIBUTION OF THE 
AIR LOAD AMONG COMPONENTS OF AIRPLANES. 
Bertram C. Wollner. April 11, 1949. 33p. diagrs., 
tab. (NACA RM L9B10) 

A VECTOR STUDY OF LINEARIZED SUPERSONIC 
FLOW APPLICATIONS TO NONPLANAR 
PROBLEMS. John C. Martin. 1953. ii, 34p. 
diagrs., tab. (NACA Rept. 1143. Formerly 
TN 2641) 



APPLICATION OF TWO-DIMENSIONAL VORTEX 
THEORY TO THE PREDICTION OF FLOW FIELDS 
BEHIND WINGS OF WING-BODY COMBINATIONS 
AT SUBSONIC AND SUPERSONIC SPEEDS. Arthur 
Wm. Rogers. September 1954. (ii), 91p. diagrs., 
photo., 3 tabs. (NACA TN 3227) 

THEORETICAL CALCULATIONS OF THE LATERAL 
STABILITY DERIVATIVES FOR TRIANGULAR VER- 
TICAL TAILS WITH SUBSONIC LEADING EDGES 
TRAVELING AT SUPERSONIC SPEEDS. Percy J. 
Bobbitt. December 1954. 68p. diagrs., photos., 
5 tabs. (NACA TN 3240) 

GENERAL THEORY OF CONICAL FLOWS AND ITS 
APPLICATION TO SUPERSONIC AERODYNAMICS. 
(La theorie generate des mouvements coniques at 
ses applications a I'aerodynamique supersonique). 
Paul Germain. PREFACE. M. J. Peres. 
January 1955. vii, 333p. diagrs. (NACA 
TM 1354. Trans, from Office National d'i:tudes et 
de Recherches Aeronautiques, Pub. 34, 1949) 

THEORETICAL CALCULATIONS OF THE PRES- 
SURES, FORCES, AND MOMENTS DUE TO 
VARIOUS LATERAL MOTIONS ACTING ON THIN 
ISOLATED VERTICAL TAILS WITH SUPERSONIC 
LEADING AND TRAILING EDGES. Kenneth 
MargoUs. March 1955. 43p. diagrs., 10 tabs. 
(NACA TN 3373) 



Steady Loads 
(4.1.1.2.1) 



MEASUREMENTS OF THE WING AND TAIL LOADS 
DURING THE ACCEPTANCE TESTS OF BELL XS-1 
RESEARCH AIRPLANE. De E. Beeler and John P. 
Mayer. April 13, 1948. 25p. diagrs., photos., 2 
tabs. (NACA RM L7L12) 



LOADS AND CONSTRUCTION 
LOADS (4. 1) 



143 



Steady Loads 
(Cont. ) 



Aerodynamic 



EFFECT OF HORIZONTAL-TAIL SPAN AND 
VERTICAL LOCATION ON THE AERODYNAMIC 
CHARACTERISTICS OF AN UNSWEPT TAIL 
ASSEMBLY IN SIDESLIP. Donald R. Riley. 1954. 
11, 20p. diagrs., photos., tab. (NACA Rept. 1171. 
Formerly TN 2907) 

CALCULATED SUBSONIC SPAN LOADS AND 
RESULTING STABILITY DERIVATIVES OF UN- 
SWEPT AND 45° SWEPTBACK TAIL SURFACES IN 
SIDESLIP AND IN STEADY ROLL. M. J. Queijo 
and Donald R. Riley. October 1954. llOp. 
diagrs., 2 tabs. (NACA TN 3245) 

PREDICTION OF DOWNWASH BEHIND SWEPT -WING 
AIRPLANES AT SUBSONIC SPEED. John De Young 
and Walter H. Barling, Jr. January 1955. 104p. 
diagrs., 3 tabs. (NACA TN 3346) 



Maneuvering 
(4,1.1.2.2) 

MEASUREMENTS OF THE WING AND TAIL LOADS 
DURING THE ACCEPTANCE TESTS OF BELL XS-1 
RESEARCH AIRPLANE. De E. Beeler and John P. 
Mayer. April 13, 1948. 25p. diagrs., photos., 2 
tabs. (NACA RM L7L12) 

A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT -WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
Seth B. Anderson and Richard S. Bray. November 
1951. 33p. diagrs., photo., tab. (NACA RM A51I12) 

THE UNSYMMETRICAL LOAD AND BENDING 
MOMENT ON THE HORIZONTAL TAIL OF A JET- 
POWERED BOMBER MEASURED IN SIDESLIPPPING 
FLIGHT. T. V. Cooney. January 1952. 19p. 
diagrs., tab. (NACA RM L51J24) 



THE VERTICAL-TAIL LOADS MEASURED DURING 
A FLIGHT INVESTIGATION ON A JET -POWERED 
BOMBER AIRPLANE. T. V. Cooney. May 1953. 
32p. diagrs., photo. (NACA RM L52G21) 

MATRIX METHODS FOR DETERMINING THE 
LONGITUDlNAL-STABILITy DERIVATIVES OF AN 
AIRPLANE FROM TRANSIENT FLIGHT DATA. 
James J. Donegan. 1954. ii, 20p. diagrs., 6 tabs. 
(NACA Kept. 1169. Formerly TN 2902) 



EFFECT OF LAG OF SJDEWASH ON THE 
VERTICAL-TAIL CONTRIBUTION TO OSCIL- 
LATORY DAMPING IN YAW OF AIRPLANE 
MODELS. Lewis R. Fisher and Herman S. 
Fletcher. January 1955. 38p. diagrs., photos. 
(NACA TN 3356) 



Buffeting and Gust 
(4.1.1.2.3) 



MEASUREMENTS OF THE WING AND TAIL LOADS 
DURING THE ACCEPTANCE TESTS OF BELL XS-1 
RESEARCH AIRPLANE. De E. Beeler and John P. 
Mayer. April 13, 1948. 25p. diagrs., photos., 2 
tabs. (NACA RM L7L12) 



STABILITY RESULTS OBTAINED WITH DOUGLAS 
D-558-1 AIRPLANE (BUAERO NO. 37971) IN 
FLIGHT UP TO A MACH NUMBER OF 0.89. 
WUliam H. Barlow and Howard C. Lilly. April 22, 
1949. 16p. diagrs., photds. (NACA RM L8K03) 

LIFT AND MOMENT CHARACTERISTICS AT SUB- 
SONIC MACH NUMBERS OF FOUR 10-PERCENT- 
THICK AIRFOIL SECTIONS OF VARYING TRAILING- 
EDGE THICKNESS. James L. Summers and William 
A. Page. December 20, 1950. 32p. diagrs., photos. 
(NACA RM A50J09) 

BUFFETING-LOAD MEASUREMENTS ON A JET- 
POWERED BOMBER AIRPLANE WITH REFLEXED 
FLAPS. John A. See and William S. Aiken, Jr. 
August 1951. 28p. diagrs., 3 tabs. (NACA 
RM L51E24a) 

PRELIMINARY INVESTIGATION OF THE PRESSURE 
FLUCTUATIONS IN THE WAKES OF TWO- 
DIMENSIONAL WINGS AT LOW ANGLES OF AT- 
TACK. Robert M. Sorenson, John A. Wyss and 
James C. Kyle. October 1951. 58p. diagrs., 
photos. (NACA RM A51G10) 

AN APPLICATION OF THE ROCKET-PROPELLED- 
MODEL TECHNIQUE TO THE INVESTIGATION OF 
LOW-LIFT BUFFETING AND THE RESULTS OF 
PRELIMINARY TESTS. Homer P. Mason and 
William N. Gardner. September 1952. 19p. 
diagrs., photos. (NACA RM L52C271 

MEASUREMENTS OF FLUCTUATING PRESSURES 
ON A 1/4-SCALE MODEL OF THE X-1 AIRPLANE 
WITH A 10-PERCENT -THICK WING IN THE 
LANGLEY 16-FdOT TRANSONIC TUNNEL. 
Louis W. Habel and Seymour Steinberg. January 
1953. 29p. diagrs., photos. (NACA RM L52J31) 

SOME MEASUREMENTS OF ATMOSPHERIC 
TURBULENCE OBTAINED FROM FLOW-DIRECTION 
VANES MOUNTED ON AN AIRPLANE. Robert G. 
Chilton. November 1954. 22p. diagrs., photo., 
tab. (NACA TN 3313) 

ESTIMATES OF PROBABILITY DISTRIBUTION OF 
ROOT -MEAN-SQUARE GUST VELOCITY OF 
ATMOSPHERIC TURBULENCE FROM OPERATION- 
AL GUST -LOAD DATA BY RANDOM -PROCESS 
THEORY. Harry Press, May T. Meadows and Ivan 
Hadlock. March 1955. 48p. diagrs., 4 tabs. 
(NACA TN 3362) 



FUSELAGE, NACELLES, 

AND CANOPIES 

(4.1.1.3) 



AN EXPERIMENTAL INVESTIGATION OF NACA 
SUBMERGED INLETS AT HIGH SUBSONIC SPEEDS. 
I - INLETS FORWARD OF THE WING LEADING 
EDGE. Charles F. Hall and F. Dorn Barclay. 
June 9, 1948. 6^. diagrs., photos. (NACA 
RM A8B16) 

AN ANALYSIS OF AVAILABLE DATA ON EFFECTS 
OF WING-FUSELAGE-TAIL AND WING-NACELLE 
INTERFERENCE ON THE DISTRIBUTION OF THE 
AIR LOAD AMONG COMPONENTS OF AIRPLANES. 
Bertram C. WoUner. April 11, 1949. 33p. diagrs., 
tab. (NACA RM L9B10) 



LOADS AND CONSTRUCTION 
144 LOADS (4. 1) 



Fuselage, Nacelles, and Canopies 
(Cont. ) 

EFFECT OF AIRFOIL SECTION AND TIP TANKS 
ON THE AERODYNAMIC CHARACTERISTICS AT 
HIGH SUBSONIC SPEEDS OF AN UNSWEPT WING 
OF ASPECT RATIO 5. 16 AND TAPER RATIO 0.61. 
H. Norman Silvers and Kenneth P. Spreemann. 
December 1, 1949. 30p. diagrs., photos., 2 tabs. 
(NACA RM L9J04) 



AN INVESTIGATION OF THREE TRANSONIC FUSE- 
LAGE AIR INLETS AT MACH NUMBERS FROM 0.4 
TO 0.94 AND AT A MACH NUMBER OF 1.19. Robert 
E. Pendley, Harold L. Robinson and Claude V. 
Williams. November 7, 1950. 51p. diagrs., photos., 
3 tabs. (NACA RM L50H24) 



LOAD DISTRIBUTION OVER A FUSELAGE IN COM- 
BINATION WITH A SWEPT WING AT SMALL 
ANGLES OF ATTACK AND TRANSONIC SPEEDS. 
Maurice D. White and Bonne C. Look. November 
1951. 26p. diagrs., photo., tab. (NACA RM 
A51H15) 



PRESSURE DISTRIBUTION AT LOW SPEED ON A 
1/4-SCALE BELL X-5 AIRPLANE MODEL. 
William B. Kemp, Jr. and Albert G. Few, Jr. 
December 1951. 86p. diagrs., photos. (NACA 
RM L51I25) 

PRESSURE DISTRIBUTIONS ON BODIES OF REVO- 
LUTION AT SUBSONIC AND TRANSONIC SPEEDS. 
Richard I. Cole. July 1952. 47p. diagrs., photos., 
tab. (NACA RM LS2D30) 



A COMPARISON OF THE EXPERIMENTAL SUB- 
SONIC PRESSURE DISTRIBUTIONS ABOUT SEV- 
ERAL BODIES OF REVOLUTION WITH PRESSURE 
DISTRIBUTIONS COMPUTED BY MEANS OF THE 
LINEARIZED THEORY. Clarence W. Matthews. 
1953. ii, 29p. diagrs., tab. (NACA Rept. 1155. 
Formerly TN 2519; RM L9F28) 



WING AND FUSELAGE LOADS MEASURED IN 
FLIGHT ON THE NORTH AMERICAN B-45 AND 
F-82 AIRPLANES. Paul W. Harper. February 
1953. 35p. diagrs., 4 tabs. (NACA RM L52L09) 



SOME NOTES ON THE AERODYNAMIC LOADS 
ASSOCIATED WITH EXTERNAL-STORE 
INSTALLATIONS. H. Norman Silvers and Thomas 
C. O'Bryan. June 1953. 17p. diagrs. (NACA 
RM L53E06a) 



OSCILLATING PRESSURES NEAR A STATIC 
PUSHER PROPELLER AT TIP MACH NUMBERS UP 
TO 1.20 WITH SPECIAL REFERENCE TO THE EF- 
FECTS OF THE PRESENCE OF THE WING. Harvey 
H. Hubbard and Leslie W. Lassiter. July 1954. 
35p. diagrs., photos., tab. (NACA TN 3202) 



AN INVESTIGATION OF SEVERAL NACA 1-SERIES 
NOSE INLETS WITH AND WITHOUT PROTRUDING 
CENTRAL BODIES AT HIGH -SUBSONIC MACH 
NUMBERS AND AT A MACH NUMBER OF 1.2. 
Robert E. Pendley and Harold L. Robinson. May 
1955. 51p. diagrs., photos. (NACA TN 3436. 
Formerly RM L9L23a) 



ROTATING WINGS 
(4.1. 1.4) 

DESCRIPTION AND INVESTIGATION OF A 
DYNAMIC MODEL OF THE XH-17 TWO-BLADE 
JET -DRIVEN HELICOPTER. George W. Brooks and 
Maurice A. Sylvester. March 14, 1951. 49p. 
diagrs., photos., 6 tabs. (NACA RM L50I21) 

REVIEW OF INFORMATION ON INDUCED FLOW OF 
A LIFTING ROTOR. Alfred Gessow. August 1954. 
16p. diagrs., photo., tab. (NACA TN 3238) 

GUST EXPERIENCE OF A HELICOPTER AND AN 
AIRPLANE IN FORMATION FLIGHT. Aimer D. 
Crim. December 1954. 12p. diagrs., photos., 
2 tabs. (NACA TN 3354) 

THE EFFECT OF CONTROL STIFFNESS AND FOR- 
WARD SPEED ON THE FLUTTER OF A 1/10-SCALE 
DYNAMIC MODEL OF A TWO-BLADE JET -DRIVEN 
HELICOPTER ROTOR. George W. Brooks and 
Maurice A. Sylvester. April 1955. 38p. diagrs., 
photo., 3 tabs. (NACA TN 3376) 

A STUDY OF NORMAL ACCELERATIONS AND 
OPERATING CONDITIONS EXPERIENCED BY 
HELICOPTERS IN COMMERCIAL AND MILITARY 
OPERATIONS. Marlin E. Hazen. April 1955. 34p. 
diagrs., photos., 5 tabs. (NACA TN 3434) 

A DYNAMIC -MODEL STUDY OF THE EFFECT OF 
ADDED WEIGHTS AND OTHER STRUCTURAL VAR- 
IATIONS ON THE BLADE BENDING STRAINS OF AN 
EXPERIMENTAL TWO-BLADE JET -DRIVEN HELI- 
COPTER IN HOVERING AND FORWARD FLIGHT. 
John Locke McCarty and George W. Brooks. May 
1955. i, 47p. diagrs., photo., 6 tabs. (NACA 
TN 3367) 



AEROELASTICITY 
(4.1.1.5) 



PRELftHNARY STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTERIS- 
TICS OF THIN WINGS. A. Gerald Ralney. July 1952. 
33p. diagrs., photo., tab. (NACA RH L52D08) 

THE CALCULATION OF CERTAIN STATIC AERO- 
ELASTIC PHENOMENA OF WINGS WITH TIP 
TANKS OR BOOM-MOUNTED LIFTING SURFACES. 
Franklin W. Diederich and Kenneth A. Foss. 
August 1952. 55p. diagrs., 2 tabs. (NACA 
RM L52A22) 

SOME OBSERVATIONS ON STALL FLUTTER AND 
BUFFETING. A. Gerald Ralney. June 1953. lip. 
diagrs. (NACA RM L53E15) 

LIFT AND MOMENT EQUATIONS FOR OSCILLAT- 
ING AIRFOILS IN AN INFINITE UNSTAGGERED 
CASCADE. Alexander Mendelson and Robert W. 
Carroll. October 1954. 46p. diagrs., 3 tabs. 
(NACA TN 3263) 

GENERALIZED INDICIAL FORCES ON DEFORMING 
RECTANGULAR WINGS IN SUPERSONIC FLIGHT. 
Harvard Lomax, Franklyn B. Fuller and Loma Sluder. 
November 1954. 74p. diagrs., tab. (NACA TN 3286) 



LOADS AND CONSTRUCTION 

LOADS (4. 1) 145 



Aeroelasticity (Cont. ) 



AN EXPLORATORY INVESTIGATION OF SOME 
TYPES OF AEROELASTIC INSTABIUTY OF OPEN 
AND CLOSED BODIES OF REVOLUTION MOUNTED 
ON SLENDER STRUTS. S. A. Clevenson, 
E. Wldmayer, Jr. and Franklin W. Diederich. 
November 1954. 44p. diagrs., photos., 3 tabs. 
(NACA TN 3308. Formerly RM L53E07) 

DESCRIPTION AND ANALYSIS OF A ROCKET - 
VEHICLE EXPERIMENT ON FLUTTER INVOLVING 
WING DEFORMATION AND BODY MOTIONS. H. J. 
Cunningham and R. R. Lundstrom. January 1955. 
26p. diagrs., photos., 2 tabs. (NACA TN 3311. 
Formerly RM L50I29) 



SOME CONSIDERATIONS ON TWO-DIMENSIONAL 
THEN AIRFOILS DEFORMING IN SUPERSONIC 
FLOW. Eugene Mlgotsky. January 1955. 36p. 
diagrs. (NACA TN 3386) 



A SIMPLIFIED METHOD FOR CALCULATING 
AEROELASTIC EFFECTS ON THE ROLL OF AIR- 
CRAFT. John M. Hedgepeth, Paul G. Waner, Jr. 
and Robert J. Kell. March 1955. 26p. diagrs., 
4 tabs. (NACA TN 3370) 

METHOD OF CONTROLLING STIFFNESS PROPER- 
TIES OF A SOLID-CONSTRUCTION MODEL WING. 
Norman S. Land and Frank T. Abbott, Jr. April 
1955. 21p. diagrs., photos., tab. (NACA TN 3423) 



LANDING 
(4.1.2) 



AN. EXPERIMENTAL INVESTIGATION OF WHEEL 
SPIN-UP DRAG LOADS. Benjamin Milwitzky, Dean 
C. Lindqulst and Dexter M. Potter. September 1954. 
18p. diagrs. (NACA TN 3246. Formerly 
RM L53E06b) 



AN EXPERIMENTAL INVESTIGATION OF THE 
EFFECT OF WHEEL PREROTATION ON LANDING- 
GEAR DRAG LOADS. Dexter M. Potter. October 
1954. 19p. diagrs., photos., tab. (NACA TN 3250) 



IMPACT 
(4.1.2.1) 



ON TRAVELING WAVES IN BEAMS. Robert W. 
Leonard and Bernard Budiansky. 1954. ill, 27p. 
diagrs. (NACA Rept. 1173. Formerly TN 2874) 



STATISTICAL MEASUREMENTS OF CONTACT 
CONDITIONS OF 478 TRANSPORT -AIRPLANE 
LANDINGS DURING ROUTINE DAYTIME OPERA- 
TIONS. Norman S. Silsby. June 1954. 32p. diagrs., 
photos., 3 tabs. (NACA TN 3194) 



Land 



(4.1.2.1.1) 



ANALYSIS OF LANDING-GEAR BEHAVIOR. 
Benjamin Milwitzky and Francis E. Cook. 1953. 
iU, 45p. diagrs., photo., 3 tabs. (NACA Rept. 1154. 
Formerly TN 2755) 



DROP HAMMER TESTS WITH THREE OLEO STRUT 
MODELS AND THREE DIFFERENT SHOCK STRUT 
OILS AT LOW TEMPERATURES. (Fallhammer- 
versuche mlt drel Olfederstrebenmustern und drei 
verschiedenen Federstrebenblen bei tlefen 
Temperaturen). Kranz, July 1954. 55p. diagrs., 
photos., 10 tabs. (NACA TM 1372. Trans, from 
Zentrale fiir wissenschaftllches Berichtswesen der 
Luftfahrtforschung, Berlin, UM 564, Jan. 17, 1939) 

CONSIDERATIONS ON A LARGE HYDRAULIC JET 
CATAPULT. Upshur T. Joyner and Walter B. 
Home. July 1954. 49p. diagrs., photos., tab. 
(NACA TN 3203. Formerly RM L51B27) 



AN EXPERIMENTAL INVESTIGATION OF WHEEL 
SPIN-UP DRAG LOADS. Benjamin Milwitzky, Dean 
C. Lindquist and Dexter M. Potter. September 1954. 
18p. diagrs. (NACA TN 3246. Formerly 
RM L53E06b) 

THE INFLUENCE OF WHEEL SPIN-UP ON 
LANDING-GEAR IMPACT. W. Fliigge and C. W. 
Coale, Stanford University. October 1954. ii, 107p. 
diagrs., 8 tabs. (NACA TN 3217. Continuation of 
TN 2743) 

AN EVALUATION OF AN ACCELEROMETER 
METHOD FOR OBTAINING LANDING-GEAR DRAG 
LOADS. Jerome G. Theisen and Philip M. Edge, Jr. 
October 1954. 22p. diagrs., photos. (NACA 
TN 3247) 

AN EXPERIMENTAL INVESTIGATION OF THE 
EFFECT OF WHEEL PREROTATION ON LANDING- 
GEAR DRAG LOADS. Dexter M. Potter. October 
1954. 19p. diagrs., photos., tab. (NACA TN 3250) 



ON FORCE -DEFLECTION DIAGRAMS OF AIR- 
PLANE SHOCK ABSORBER STRUTS. FIRST, 
SECOND, AND THIRD PARTIAL REPORTS. (Zur 
Kenntnis der Kraftwegdiagramme von 
Flugzeugfederbeinen). K. Schlaefke. November 
1954. 48p. diagrs., 4 tabs. (NACA TM 1373. 
Trans, from Technische Berichte, v. 11, nos. 2, 4, 
& 5, 1944) 

AN EXPERIMENTAL STUDY OF ORIFICE. COEF- 
FICIENTS, INTERNAL STRUT PRESSURES, AND 
LOADS ON A SMALL OLEO -PNEUMATIC SHOCK 
STRUT. James H. Walls. April 1955. 23p. 
diagrs., photos. (NACA TN 3426) 

A STUDY OF NORMAL ACCELERATIONS AND 
OPERATING CONDITIONS EXPERIENCED BY 
HELICOPTERS IN COMMERCUL AND MILITARY 
OPERATIONS. Marlin E. Hazen. April 1955. 34p. 
diagrs., photos., 5 tabs. (NACA TN 3434) 



A STATISTICAL STUDY OF WING LIFT AT GROUND 
CONTACT FOR FOUR TRANSPORT AIRPLANES. 
Dean C. Lindqulst. April 19S5. 18p. diagrs., tab. 
(NACA TN 3435) 



LOADS AND CONSTRUCTION 
146 LOADS (4.1) 



Water 



(4.1.2.1.2) 



THEORY AND PROCEOUHE FOR DETERMINING 
LOADS AND MOTIONS IN CHDJE -IMMERSED 
HYDRODYNAMIC IMPACTS OF PRISMATIC 
BODIES. Emanuel Schnitaer. 1953. U, 29p. 
diagrs. (NACA Rept. 1152. Formerly TN 2813) 



GROUND- RUN 
(4.1.2. 2) 

EXPERIMENTS ON TAIL-WHEEL SHIMMY. 
(Experimentelle Untersuchungen iiber das 
Spornradflattern). O. Dietz and R. Harling. 
October 1954. 81p. diagrs., photos. (NACA 
TM 1376. Trans, from Zentrale fiir 
weissenschaftUches Berichtswesen der 
Luftfahrtforschung, Berlin, FB 1320) 

SOME MEASUREMENTS AND POWER SPECTRA OF 
RUNWAY ROUGHNESS. James H. Walls, John C. 
Houbolt and Harry Press. November 1954. 27p. 
diagrs., tab. (NACA TN 3305) 



Land 



(4.1.2.2.1) 

PAPERS ON SHIMMY AND ROLLING BEHAVIOR OF 
LANDING GEARS PRESENTED AT STUTTGART 
CONFERENCE OCT. 16 AND 17, 1941. (Bericht iiber 
die Sitzung Flattern und RoUverhalten von 
Fahrwerken am 16. /17. Oktober 1941 in Stuttgart). 
August 1954. ii, 233p. diagrs. , photos. , 2 tabs. 
(NACA TM 1365. Trans, from Lilienthal- 
Gesellschaft fur Luftfahrtforschung, Berlin, 
Bericht 140) 

LOW -SPEED YAWED-ROLLING AND SOME OTHER 
ELASTIC CHARACTERISTICS OF TWO 56-INCH- 
DIAMETER, 24-PLY -RATING AIRCRAFT TIRES. 
Walter B. Home, Bertrand H. Stephenson and Robert 
F. Smiley. August 1954. 108p. diagrs., photos., 6 
tabs. (NACA TN 3235) 



EXPERIMENTS ON TAIL-WHEEL SHIMMY. 
(Experimentelle Untersuchungen iiber das 
Spornradflattern). O. Dietz and R. Harling. 
October 1954. 81p. di^rs., photos. (NACA 
TM 1376. Trans, from Zentrale fiir 
weissenschaftUches Berichtswesen der 
Luftfahrtforschimg, Berlin, FB 1320) 



DETERMINATION OF THE ELASTIC CONSTANTS 
OF AIRPLANE TIRES. (Ermittlung der elastischen 
Konstanten von Flugzeugreifen). Boeckh. November 
1954. 39p. diagrs. (NACA TM 1378. Trans, from 
Focke-Wulf Flugzeugbau G.m.b.H, Bremen, 
V.13.3703) 



CONTRIBUTION TO THE THEORY OF TAIL- 
WHEEL SHIMMY. (Beitrag zur Theorie des 
Spornradflatterns). M. Melzer. December 1954. 
37p. diagrs., 7 tabs. (NACA TM 1380. Trans, from 
Focke-Wulf Flugzeugbau G. m. b. H., Bremen, 
Technische Berichte, v. 7, no. 2, 1940) 



PRELANDING CONDITIONS 
(4. 1.2.3) 



A STUDY OF NORMAL ACCELERATIONS AND 
OPERATING CONDITIONS EXPERIENCED BY 
HELICOPTERS IN COMMERCUL AND MILITARY 
OPERATIONS. Marlin E. Hazen. April 1955. 34p. 
diagrs., photos., 5 tabs. (NACA TN 3434) 



A STATISTICAL STUDY OF WING LIFT AT GROUND 
CONTACT FOR FOUR TRANSPORT AIRPLANES. 
Dean C. Lindquist. April 1955. 18p. diagrs., tab. 
(NACA TN 3435) 



LOADS AND CONSTRUCTION 147 



Vibration and Flutter 
(4.2) 



A TORSIONAL STIFFNESS CRITERION FOR PRE- 
VENTING FLUTTER OF W1NG8 OF SUPERSONIC 
MISSILES. Bernard Budiansky, Joseph N. Kotanchik 
and Patrick T. Chiarito. August 28, 1947. 14p. 
diagrs., tab. (NACA HM L7G02) 



NOTE ON FLUTTER OF A 60° DELTA WING 
ENCOUNTERED AT LOW-SUPERSONIC SPEEDS 
DURING THE FUGHT OF A ROCKET-PROPELLED 
MODEL. WUliam T. Lauten, Jr. and Grady L. 
Mitcham. May 14, 1951. 21p. diagrs., photos., 
5 tabs. (NACA RM L51B28) 



EXPERIMENTAL INVESTIGATION OF THE VIBRA- 
TION CHARACTERISTICS OF FOUR DESIGNS OF 
TURBINE BLADES AND OF THE EFFECT PRO- 
DUCED BY VARYING THE AXIAL SPACING 
BETWEEN NOZZLE BLADES AND TURBINE 
BLADES. W. C. Morgan and C. R. Morse. 
February 1952. 28p. diagrs., photos., tab. (NACA 
RM E51J25) 

AN ANALYSE OF THE EFFECT OF STRUCTURAL 
FEEDBACK ON THE FLUTTER OF A CONTROL 
SURFACE HAVING POWER-BOOST SYSTEM. 
Robert H. Barnes. June 1952. 29p. diagrs., photos. 
(NACA RM A51I25) 



AN APPLICATION OF THE ROCKET -PROPELLED- 
MODEL TECHNIQUE TO THE INVESTIGATION OF 
LOW-LIFT BUFFETING AND THE RESULTS OF 
PRELIMINARY TESTS. Homer P. Mason and 
William N. Gardner. September 1952. 19p. 
diagrs., photos. (NACA RM L52C27) 

TORSIONAL VIBRATIONS OF HOLLOW THIN- 
WALLED CYLINDRICAL BEAMS. Edwin T. 
Kruszewski and Eldon E. Kordes. August 1954. 33p. 
diagrs., tab. (NACA TN 3206) 



EXPERIMENTS ON TAIL-WHEEL SHIMMY. 
(Experimentelle Untersuchungen iiber das 
Spornradflattern). O. Dietz and R. Harling. 
October 1954. 81p. diagrs., photos. (NACA 
TM 1376. Trans, from Zentrale fur 
weissenschaftUches Berichtswesen der 
Luftfahrtforschung, Berlin, FB 1320) 

COMPARISON OF FLUTTER CALCULATIONS USING 
VARIOUS AERODYNAMIC COEFFICIENTS WITH 
EXPERIMENTAL RESULTS FOR SOME RECTANGU- 
LAR CANTILEVER WINGS AT MACH NUMBER 1.3. 
Herbert C. Nelson and Ruby A. Rainey. November 
1954. 22p. diagrs., 2 tabs. (NACA TN 3301) 

DESCRIPTION AND ANALYSIS OF A ROCKET- 
VEHICLE EXPERIMENT ON FLUTTER INVOLVING 
WING DEFORMATION AND BODY MOTIONS. H. J. 
Cunningham and R. R. Lundstrom. January 1955. 
26p. diagrs., photos., 2 tabs. (NACA TN 3311. 
Formerly RM L50I29) 



METHOD OF CONTROLLING STIFFNE^ PROPER- 
TIES OF A SOLID-CONSTRUCTION MODEL WING. 
Norman S. Land and Frank T. Abbott, Jr. April 
1955. 21p. diagrs., photos., tab. (NACA TN 3423) 



WINGS AND AILERONS 
(4.2.1) 



OBSERVATIONS ON AN AILERON-FLUTTER IN- 
STABILITY ENCOUNTERED ON A 45° SWEPT- 
BACK WING IN TRANSONIC AND SUPERSONIC 
FUGHT. Marvin Pitkin, WilUam N. Gardner and 
Howard J. Curfman, Jr. April 11, 1947. 23p. 
diagrs., photos. (NACA RM L6L09) 



AN INVESTIGATION OF AILERON OSCILLATIONS 
AT TRANSONIC SPEEDS ON NACA 23012 AND 
NACA 65-212 AIRFOILS BY THE WING-FLOW 
METHOD. Harold L. Crane. December 29, 1948. 
9p. diagrs., photo. (NACA RM L8K29) 



SOME WIND-TUNNEL EXPERIMENTS ON SINGLE 
DEGREE OF FREEDOM FLUTTER OF AILERONS 
IN THE HIG8H SUBSONIC SPEED RANGE. Sherman 
A. Clevenson. March 30, 1949. 33p. diagrs., 
photo., 3 tabs. (NACA RM L9B08) 



LOW-SPEED TESTS OF A MODEL SIMULATING 
THE PHENOMENON OF CONTROL-SURFACE 
BUZZ. William H. PhlUips and James J. Adams. 
August 16, 1950. 16p. diagrs., photo. (NACA 
RM L50F19) 

INVESTIGATION OF A 42.7° SWEPTBACK WING 
MODEL TO DETERMINE THE EFFECTS OF 
TRAILING-EDGE THICKNESS ON THE AILERON 
HINGE -MOMENT AND FLUTTER CHARACTER- 
ISTICS AT TRANSONIC SPEEDS. Robert F. 
Thompson. December 26, 1950. 42p. diagrs., 
photos., 2 tabs. (NACA RM L50J06) 

EXPERIMENTAL STUDY OF THE EFFECT OF 
SWEEPBACK ON TRANSONIC AILERON FLUTTER. 
Lionel L. Levy, Jr. and Earl D. Knechtel. 
September 1951. 20p. diagrs., photo. (NACA RM 
A51E04) 

FLUTTER INVESTIGATION OF TWO THIN, LOW- 
ASPECT-RATIO, SWEPT, SOLID, METAL WINGS 
IN THE TRANSONIC RANGE BY USE OF A FREE- 
FALLING BODY. W. T. Lauten, Jr. and Maurice 
A. Sylvester. February 1952. 12p. diagrs., photo., 
2 tabs. (NACA RM L51K28a) 

PRELIMINARY STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTERIS- 
TICS OF THIN WINGS. A. Gerald Rainey. July 1952. 
33p. diagrs., photo., tab. (NACA RM L52D08) 



THE CALCULATION OF CERTAIN STATIC AERO- 
ELASTIC PHENOMENA OF WINGS WITH TIP 
TANKS OR BOOM-MOUNTED LIFTING SURFACES. 
Franklin W. Diederich and Kenneth A. Foss. 
August 1952. 55p. diagrs., 2 tabs. (NACA 
HM L52A22) 



LOADS AND CONSTRUCTION 
148 VIBRATION AND FLUTTER (4. 2) 



Wings and Ailerons {Cont. ) 



CONSIDERATIONS ON THE EFFECT OF WIND- 
TUNNEL WALLS ON OSCILLATING AIR FORCES 
FOR TWO-DIMENSIONAL SUBSONIC COMPRES- 
SIBLE FLOW. Harry L. Runyan and Charles E. 
Watklns. 1953. ii, 7p. diagrs. (NACA Rept. 1150. 
Formerly TN 2552) 

SOME OBSERVATIONS ON STALL FLUTTER AND 
BUFFETING. A. Gerald Rainey. June 1953. lip. 
diagrs. (NACA RM L53E15) 

GENERALIZED INDICIAL FORCES ON DEFORMING 
RECTANGULAR WINGS IN SUPERSONIC FLIGHT. 
Harvard Lomax, Franklyn B. Fuller and Loma Sluder. 
November 1954.74p. diagrs., tab. (NACA TN 3286) 

INITIAL EXPERIMENTS ON FLUTTER OF IM- 
SWEPT CANTILEVER WINGS AT MACH NUMBER 
1.3. W. J. Tuovila, John E. Baker and Arthur A. 
Regier. November 1954. 19p. diagrs., photos., 
2 tabs. (NACA TN 3312. Formerly RM L8J11) 

SOME CONSIDERATIONS ON TWO-DIMENSIONAL 
THIN AIRFOILS DEFORMING IN SUPERSONIC 
FLOW. Eugene Migotsky. January 1955. 36p. 
diagrs. (NACA TN 3386) 

TOTAL LIFT AND PITCHING MOMENT ON THIN 
ARROWHEAD WINGS OSCILLATING IN SUPERSONIC 
POTENTIAL FLOW. H. J. Cunningham. May 1955. 
43p. diagrs., 4 tabs. (NACA TN 3433) 

ON THE KERNEL FimCTION OF THE INTEGRAL 
EQUATION RELATING LIFT AND DOWNWASH DB- 
TRIBUTIONS OF OSCILLATING WINGS IN SUPER- 
SONIC FLOW. Charles E. Watkins and Julian H. 
Berman. May 1955. 43p. (NACA TN 3438) 



TAILS 
(4.2.2) 



ELEVATORS AND RUDDERS 
(4.2.2.1) 



AN ANALYSIS OF THE EFFECT OF STRUCTURAL 
FEEDBACK ON THE FLUTTER OF A CONTROL 
SURFACE HAVING POWER-BOOST SYSTEM. 
Robert H. Barnes. June 1952. 29p. diagrs., photos. 
(NACA RM A51I25) 



BODIES 
(4.2.3) 



AN EXPLORATORY INVESTIGATION OF SOME 
TYPES OF AEROELASTIC INSTABILITY OF OPEN 
AND CL<^ED BODIES OF REVOLUTION MOUNTED 
ON SLENDER STRUTS. S. A. Clevenson, 
E. Widmayer, Jr. and Franklin W. Diederich. 
November 1954. 44p. diagrs., photos., 3 tabs. 
(NACA TN 3308. Formerly RM L53E07) 



EFFECTIVE MOMENT OF INERTIA OF FLUID IN 
OFFSET, INCLINED, AND SWEPT -WING TANKS 
UNDERGOING PITCHING OSCILLATIONS. James 
R. Reese and John L. Sewall. January 1955. 27p. 
diagrs., 6 tabs. (NACA TN 3353) 



PROPELLER, FANS, AND 

COMPRESSORS 

(4.2.4) 



AN INVESTIGATION OF PROPELLER VIBRATIONS 
EXCITED BY WING WAKES. W. H. Gray and 
William Solomon. January 1952. 31p. diagrs., 
photo., tab. (NACA RM L51G13) 



PRELIMINARY STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTERIS- 
TICS OF THIN WINGS. A. Gerald Rainey. July 1952. 
33p. diagrs., photo., tab. (NACA RM L52D08) 



SOME TORSIONAL-DAMPING MEASUREMENTS OF 
LAMINATED BEAMS AS APPLIED TO THE 
PROPELLER STALL-FLUTTER PROBLEM. 
Atwood R. Heath, Jr. April 1953. 14p. diagrs., 
photos., tab. (NACA RM L53A19) 



LIFT AND MOMENT EQUATIONS FOR OSCILLAT- 
ING AIRFOILS IN AN INFINITE UNSTAGGERED 
CASCADE. Alexander Mendelson and Robert W. 
Carroll. October 1954. 46p. diagrs., 3 tabs. 
(NACA TN 3263) 



THE EFFECTS OF VARIOUS PARAMETERS, 
INCLUDING MACH NUMBER, ON PROPELLER- 
BLADE FLUTTER WITH EMPHASIS ON STALL 
FLUTTER. John E. Baker. January 1955. 40p. 
diagrs., 3 tabs. (NACA TN 3357. Formerly 
RM L50L12b) 



ON THE CALCULATION OF THE 1- P OSCILLATING 
AERODYNAMIC LOADS ON SINGLE -ROTATION 
PROPELLERS IN PITCH ON TRACTOR AIRPLANES. 
Vernon L. Rogallo and Paul F. Yaggy. May 1955. 
28p. diagrs., photo. (NACA TN 3395) 



ROTATING-WING 
AIRCRAFT 

(4.2.5) 



DESCRIPTION AND INVESTIGATION OF A 
DYNAMIC MODEL OF THE XH-17 TWO-BLADE 
JET-DRIVEN HELICOPTER. George W. Brooks and 
Maurice A. Sylvester. March 14, 1951. 49p. 
diagrs., photos., 6 tabs. (NACA RM L50I21) 



LOADS AND CONSTRUCTION 
VIBRATION AND FLUTTER (4. 2) 



149 



Rotating-Wing Aircraft (Cont. ) 



RAPID ESTIMATION OF BENDING FREQUENCIES 

OF ROTATING BEAMS. Robert T. Yntema. 

August 1954. 18p. diagrs., tab. (NACA RM L54G0^ 



REVIEW OF INFORMATION ON INDUCED FLOW OF 
A LIFTING ROTOR. Alfred Gessow. August 1954. 
16p. diagrs., photo., tab. (NACA TN 3238) 



THE EFFECT OF CONTROL STIFFNESS AND FOR- 
WARD SPEED ON THE FLUTTER OF A 1/10-SCALE 
DYNAMIC MODEL OF A TWO-BLADE JET -DRIVEN 
HELICOPTER ROTOR. George W. Brooks and 
Maurice A. Sylvester. April 1955. 38p. diagrs., 
photo., 3 tabs. (NACA TN 3376) 



A DYNAMIC-MODEL STUDY OF THE EFFECT OF 
ADDED WEIGHTS AND OTHER STRUCTURAL VAR- 
UTIONS ON THE BLADE BENDING STRAINS OF AN 
EXPERIMENTAL TWO-BLADE JET -DRIVEN HELI- 
COPTER IN HOVERING AND FORWARD FLIGHT. 
John Locke McCarty and George W. Brooks. May 
1955. i, 47p. diagrs., photo., 6 tabs. (NACA 
TN 3367) 



150 LOADS AND CONSTRUCTION 



Structures 
(4.3) 



COLUMNS 
(4.3.1) 



AN INVESTIGATION OF THE CREEP LIFETIME OF 
75S-T6 ALUMINUM -ALLOY COLUMNS. Eldon E. 
Mathauser and William A. Brooks, Jr. July 1954. 
28p. diagrs., photos., tab. (NACA TN 3204) 



FRAMES, GRIDWORKS, AND 
TRUSSES 
(4.3.2) 



BENDING TESTS ON BOX BEAMS HAVING SOLID- 
AND OPEN -CONSTRUCTION WEBS. Aldie E. 
Johnson, Jr. August 1954. 25p. diagrs., photos., 2 
tabs. (NACA TN 3231) 



PLATES 
(4.3.3) 



FLAT 
(4.3.3. 1) 



METHOD OF CONTROLLING STIFFNESS PROPER- 
TIES OF A SOLID -CONSTRUCTION MODEL WING. 
Norman S. Land and Frank T. Abbott, Jr. April 
1955. 21p. diagrs., photos., tab. (NACA TN 3423) 



Unstiffened 
(4.3.3.1.1) 

ANALYSIS OF BEHAVIOR OF SIMPLY SUPPORTED 
FLAT PLATES COMPRESSED BEYOND THE 
BUCKLING LOAD INTO THE PLASTIC RANGE. 
J. Mayers and Bernard Budiansky. February 1955. 
44p. diagrs. (NACA TN 3368) 



Stiffened 



(4.3.3.1.2) 



TESTS OF BONDED AND RIVETED SHEET- 
STRINGER PANELS. Leonard Mordfin and I. E. 
Wilks, National Bureau of Standards. Jvine 1954. 
45p. diagrs., photos., 5 tabs. (NACA TN 3215) 



BENDING TESTS ON BOX BEAMS HAVING SOLID- 
AND OPEN-CONSTRUCTION WEBS. Aldie E. 
Johnson, Jr. August 1954. 25p. diagrs., photos., 2 
tabs. (NACA TN 3231) 

AN ANALYSIS OF THE STABILITY AND ULTIMATE 
BENDING STRENGTH OF MULTIWEB BEAMS WITH 
FORMED-CHANNEL WEBS. Joseph W. Semonian 
and Roger A. Anderson. August 1954. 28p. diagrs., 
photos. (NACA TN 3232) 

AN ANALYSIS OF THE STABILITY AND ULTIMATE 
COMPRESSIVE STRENGTH OF SHORT SHEET- 
STRINGER PANELS WITH SPECIAL REFERENCE 
TO THE INFLUENCE OF RIVETED CONNECTION 
BETWEEN SHEET AND STRINGER. Joseph W. 
Semonian and James P. Peterson. March 1955. 
49p. diagrs., tab. (NACA TN 3431) 



CURVED 
(4. 3. 3. 2) 



Unstiffened 
(4.3.3.2.1) 

A NONLINEAR THEORY OF BENDING AND BUCK- 
LING OF THIN ELASTIC SHALLOW SPHERICAL 
SHELLS. A. Kaplan and Y. C. Fung, California 
Institute of Technology. August 1954. 58p. diagrs., 
photo., 5 tabs. (NACA TN 3212) 



BEAMS 
(4.3.4) 



ON TRAVELING WAVES IN BEAMS. Robert W. 
Leonard and Bernard Budiansky. 1954. iii, 27p. 
diagrs. (NACA Rept. 1173. Formerly TN 2874) 



RAPID ESTIMATION OF BENDING FREQUENCIES 

OF ROTATING BEAMS. Robert T. Yntema. 

August 1954. 18p. diagrs., tab. (NACA RM L54G03 



TORSIONAL VIBRATIONS OF HOLLOW THIN- 
WALLED CYLINDRICAL BEAMS. Edwin T. 
Kruszewski and Eldon E. Kordes. August 1954, 33p. 
diagrs., tab. (NACA TN 3206) 



STRESS DISTRIBUTIONS CAUSED BY THREE TYPES 
OF LOADING ON A CIRCULAH SEMMONOCOQUE 
CYLINDER WITH FLEXIBLE RINGS. Harvey G. 
McComb, Jr. September 1954. 54p. diagrs. (NACA 
TN 3199) 



LOADS AND CONSTRUCTION 
STRUCTURES (4. 3) 



151 



BOX 

(4.3.4,1) 

BENDING TESTS ON BOX BEAMS HAVING SOLID- 
AND OPEN-CONSTRUCTION WEBS. Aldle E. 
Johnson, Jr. August 1954. 25p. diagrs., photos., 2 
tabs. (NACATN3231) 

AN ANALYSIS OF THE STABILITY AND ULTIMATE 
BENDING STRENGTH OF MULTIWEB BEAMS WITH 
FORMED-CHANNEL WEBS. Joseph W. Semonian 
and Roger A. Anderson. August 1954. 28p. diagrs., 
photos. (NACA TN 3232) 

INVESTIGATION OF STATIC STRENGTH AND 
CREEP BEHAVIOR OF AN ALUMINUM -ALLOY 
MULTIWEB BOX BEAM AT ELEVATED TEMPER- 
ATURES. Eldon E. Mathauser. November 1954. 
21p. diagrs., photos., 4 tabs. (NACA TN 3310) 



SHELLS 
(4.3.5) 



A NONLINEAR THEORY OF BENDING AND BUCK- 
LING OF THIN ELASTIC SHALLOW SPHERICAL 
SHELLS. A. Kaplan and Y. C. Fung, California 
Institute of Technology. August 1954. 58p. diagrs., 
photo., 5 tabs. (NACA TN 3212) 

ELECTRICAL ANALOGIES FOR STIFFENED 
SHELLS WITH FLEXIBLE RINGS. R. H. MacNeal, 
California Institute of Technology. December 1954. 
35p. diagrs., 2 tabs. (NACA TN 3280) 



CYLINDERS 
(4.3.5.1) 

TORSIONAL VIBRATIONS OF HOLLOW THIN- 
WALLED CYLINDRICAL BEAMS. Edwin T. 
Kruszewski and Eldon E. Kordes. August 1954. 33p. 
diagrs., tab. (NACA TN 3206) 



Circular 
(4.3.5.1. 1) 

EXPERIMENTAL STRESS ANALYSIS OF 
STIFFENED CYLINDERS WITH CUTOUTS. SHEAR 
LOAD. Floyd R. Schlechte and Richard Rosecrans. 
July 1954. 87p. diagrs., photo., 13 tabs. (NACA 
TN 3192) 

STREIffi DISTRIBUTIONS CAUSED BY THREE TYPES 
OF LOADING ON A CIRCULAH SEMIMONOCOQUE 
CYLINDER WITH FLEXIBLE RINCS. Harvey G. 
McComb, Jr. September 1954. 54p. diagrs. (NACA 
TN 3199) 

STRESS ANALYSIS OF CIRCULAH SEMIMONO- 
COQUE CYLINDERS WITH CUTOUTS BY A PER- 
TURBATION LOAD TECHNIQUE. Harvey G. 
McComb, Jr. September 1954. 37p. diagrs., 3 tabs. 
(NACA TN 3200) 



PRELIMINARY INVESTIGATION OF THE FAILURE 
OF PRESSURIZED STIFFENED CYLINDERS. 
Norris F. Dow and Roger W. Peters. May 1955. 
14p. diagrs., photos., tab. (NACA RM L55D15b) 



CONNECTIONS 
(4.3.6) 



EFFECT OF PRESSURE ON THERMAL CONDUC- 
TANCE OF CONTACT JOINTS. Martin E. 
Barzelay, Kin Nee Tong and George F. HoUoway, 
Syracuse University. May 1955. 52p. diagrs., 
2 tabs. (NACA TN 3295) 

PRELIMINARY INVESTIGATION OF PROPERTIES 
OF HIGH-TEMPERATURE BRAZED JOINTS PRO- 
CESSED IN VACUUM OR IN MOLTEN SALT. C. A. 
Gyorgak and A. C. Francisco. May 1955. 29p. 
diagrs., photos., 7 tabs. (NACA TN 3450) 



BOLTED 
(4.3.6. 1) 

ADDITIONAL STATIC AND FATIGUE TESTS OF 
HIGH-STRENGTH ALIMINUM-ALLOY BOLTED 
JOINTS. E. C. Hartmann, Marshall Holt and I. D. 
Eaton, Aluminum Company of America. July 1954. 
42p. diagrs., photos., 7 tabs. (NACA TN 3269) 



RIVETED 
(4.3.6.2) 



AN ANALYSIS OF THE STABUL,ITY AND ULTIMATE 
COMPRESSIVE STRENGTH OF SHORT SHEET- 
STRINGER PANELS WITH SPECIAL REFERENCE 
TO THE INFLUENCE OF RIVETED CONNECTION 
BETWEEN SHEET AND STRINGER. Joseph W. 
Semonian and James P. Peterson. March 1955. 
49p. diagrs., tab. (NACA TN 3431) 



LOADS AND STRESSES 
(4.3.7) 



EXPERIMENTAL STRESS ANALYSIS OF 
STIFFENED CYLINDERS WITH CUTOUTS. SHEAR 
LOAD. Floyd R. Schlechte and Richard Rosecrans. 
July 1954. 87p. diagrs., photo., 13 tabs. (NACA 
TN 3192) 



LOADS AND CONSTRUCTION 
152 STRUCTURES (4. 3) 



Loads and Stresses (Cont. ) 



STRESS DBTRTOUTIONS CAUSED BY THREE TYPES 
OF LOADING ON A CIRCULAR SEMIMONOCOQUE 
CYLINDER WITH FLEXffiLE RINGS. Harvey G. 
McComb, Jr. September 1954. 54p. diagrs. (NACA 
TN 3199) 

STRESS ANALYSIS OF CIRCULAR SEMIMONO- 
COQUE CYLINDERS WITH CUTOUTS BY A PER- 
TURBATION LOAD TECHNIQUE. Harvey G. 
McComb, Jr. September 1954. 37p. diagrs., 3 tabs. 
(NACA TN 3200) 



COMPRESSION 
(4.3.7.2) 

TESTS OF BONDED AND RIVETED SHEET- 
STRINGER PANELS. Leonard Mordfin and I. E. 
Wllks, National Bureau of Standards. June 1954. 
45p. diagrs., photos., 5 tabs. (NACA TN 3215) 

AN ANALYSIS OF THE STABILITY AND ULTIMATE 
BENDING STRENGTH OF MULTIWEB BEAMS WITH 
FORMED-CHANNEL WEBS. Joseph W. Semonian 
and Roger A. Anderson. August 1954. 28p. diagrs., 
photos. (NACA TN 3232) 

ANALYSIS OF BEHAVIOR OF SIMPLY SUPPORTED 
FLAT PLATES COMPRESSED BEYOND THE 
BUCKLING LOAD INTO THE PLASTIC RANGE. 
J. Mayers and Bernard Budiansky. February 1955. 
44p. diagrs. (NACA TN 3368) 

AN ANALYSIS OF THE STABILITY AND ULTIMATE 
COMPRESSIVE STRENGTH OF SHORT SHEET- 
STRINGER PANELS WITH SPECIAL REFERENCE 
TO THE INFLUENCE OF RIVETED CONNECTION 
BETWEEN SHEET AND STRINGER. Joseph W. 
Semonian and James P. Peterson. March 1955. 
49p. diagrs., tab. (NACA TN 3431) 



BENDING 
(4.3.7.3) 

BENDING TESTS ON BOX BEAMS HAVING SOLID- 
AND OPEN-CONSTRUCTION WEBS. Aldie E. 
Johnson, Jr. August 1954. 25p. diagrs., photos., 2 
tabs. (NACA TN 3231) 

AN ANALYSIS OF THE STABILITY AND ULTIMATE 
BENDING STRENGTH OF MULTIWEB BEAMS WITH 
FORMED-CHANNEL WEBS. Joseph W. Semonian 
and Roger A. Anderson. August 1954. 28p. diagrs., 
photos. (NACA TN 3232) 



TORSION 
(4.3.7.4) 



A TORSIONAL STIFFNESS CRITERION FOR PRE- 
VENTING FLUTTER OF WINGS OF SUPERSONIC 
MISSILES. Bernard Budiansky, Joseph N. Kotanchlk 
and Patrick T. Chiarito. August 28, 1947. 14p. 
diagrs., tab. (NACA RM L7G02) 



SHEAR 
(4.3.7. 5) 

EXPERIMENTAL STRESS ANALYSIS OF 
STIFFENED CYLINDERS WITH CUTOUTS. SHEAR 
LOAD. Floyd R. Schlechte and Richard Rosecrans. 
July 1954. 87p. diagrs., photo., 13 tabs. (NACA 
TN3192) 



CONCENTRATED 
(4.3.7.6) 



SOME OBSERVATIONS ON LOSS OF STATIC 
STRENGTH DUE TO FATIGUE CRACKS. Walter Illg 
and Herbert F. Hardrath. May 1955. 8p. diagrs. 
(NACA RM L55D15a) 



DYNAMIC 
(4.3.7.7) 



A STUDY OF THE APPLICATION OF POWER - 
SPECTRAL METHODS OF GENERAUZED HARMON- 
IC ANALYSIS TO GUST LOADS ON AIRPLANES. 
Harry Press and Bernard Mazelsky. 1954. ii, 17p. 
diagrs., 2 tabs. (NACA Rept. 1172. Formerly 
TN 2853) 

AN INVESTIGATION OF THE USE OF ROCKET- 
POWERED MODELS FOR GUST -LOAD STUDIES 
WITH AN APPLICATION TO A TAILLESS SWEPT- 
WING MODEL AT TRANSONIC SPEEDS. A. James 
Vitale, H. Press and C. C. Shufflebarger. June 
1954. 36p. diagrs., photos., tab. (NACA TN 3161) 

RAPID ESTIMATION OF BENDING FREQUENCIES 

OF ROTATING BEAMS. Robert T. Yntema. 

August 1954. 18p. diagrs., tab. (NACA RM L54G0? 

TORSIONAL VIBRATIONS OF HOLLOW THIN - 
WALLED CYLINDRICAL BEAMS. Edwin T. 
Kruszewski and Eldon E. Kordes. August 1954. 33p. 
diagrs., tab. (NACA TN 3206) 

AN EXPERIMENTAL INVESTIGATION OF WHEEL 
SPIN-UP DRAG LOADS. Benjamin Milwitzky, Dean 
C. Llndqulst and Dexter M. Potter. September 1954. 
18p. diagrs. (NACA TN 3246. Formerly 
RM L53E06b) 



Repeated 
(4.3.7.7. 1) 



ADDITIONAL STATIC AND FATIGUE TESTS OF 
HIGH -STRENGTH ALUMINUM-ALLOY BOLTED 
JOINTS. E. C. Hartmann, Marshall Holt and I. D. 
Eaton, Aluminum Company of America. July 1954. 
42p. diagrs., photos., 7 tabs. (NACA TN 3269) 

ESTIMATES OF PROBABILITY DISTRIBUTION OF 
ROOT -MEAN-SQUARE GUST VELOCITY OF 
ATMOSPHERIC TURBULENCE FROM OPERATION- 
AL GUST -LOAD DATA BY RANDOM -PROCESS 
THEORY. Harry Press, May T. Meadows and Ivan 
Hadlock. March 1955. 48p. diagrs., 4 tabs. 
(NACA TN 3362) 



LOADS AND CONSTRUCTION 
STRUCTURES (4. 3) 



153 



Repeated - Dynamic (Cont. ) 



PRELIMINARY INVESTIGATION OF THE FAILURE 
OF PRESSURIZED STIFFENED CYLINDEHS. 
Norrls F. Dow and Roger W. Peters. May 1955. 
14p. diagrs., photos., tab. (NACA RM L55D15b) 

A DYNAMIC -MODEL STUDY OF THE EFFECT OF 
ADDED WEIGHTS AND OTHER STRUCTURAL VAR- 
IATIONS ON THE BLADE BENDING STRAINS OF AN 
EXPERIMENTAL TWO-BLADE JET -DRIVEN HELI- 
COPTER IN HOVERING AND FORWARD FLIGHT. 
John Locke McCarty and George W. Brooks. May 
1955. i, 47p. diagrs., photo., 6 tabs. (NACA 
TN 3367) 



Transient 



(4.3.7.7.2) 



ANALYSIS OF LANDING-GEAR BEHAVIOR. 
Benjamin Milwitzky and Francis E. Cook. 1953. 
iii, 45p. diagrs., photo., 3 tabs. (NACA Rept. 1154. 
Formerly TN 2755) 



ON TRAVELING WAVES IN BEAMS. Robert W. 
Leonard and Bernard Budiansky. 1954. lit, 27p. 
diagrs. (NACA Rept. 1173. Formerly TN 2874) 



NORMAL PRESSURES 
(4.3.7.8) 



A NONUNEAR THEORY OF BENDING AND BUCK- 
LING OF THIN ELASTIC SHALLOW SPHERICAL 
SHELLS. A. Kaplan and Y. C. Fung, California 
Institute of Technology. August 1954. 58p. diagrs., 
photo., 5 tabs. (NACA TN 3212) 



MATERIALS 
(5) 




MATERIALS (5.1) 155 



Types 

(5.1) 



EXPERIMENTAL INVESTIGATION OF AIR-FLOW 
UNIFORMITY AND PRESSURE LEVEL ON WIRE 
CLOTH FOR TRANSPIRATION-COOLING APPLICA- 
TIONS. Patrick L. Donoughe and Roy A. McKinnon. 
July 1952. 28p. dlagrs., photos., tab. (NACA 
RM E52E16) 



ALUMINUM 
(5.1.1) 



TIME -TEMPERATURE PARAMETERS AND AN 
APPLICATION TO RUPTURE AND CREEP OF 
ALUMINUM ALLOYS. George J. HeimerL June 
1954. 35p. diagrs., tab. (NACA TN 3195) 

ADDITIONAL STATIC AND FATIGUE TESTS OF 
HIGH-STRENGTH ALUMINUM -ALLOY BOLTED 
JOINTS. E. C. Hartmann, Marshall Holt and I. D. 
Eaton, Aluminum Company of America. July 1954. 
42p. dlagrs., photos., 7 tabs. (NACA TN 3269) 

AN EXPERIMENTAL AND THEORETICAL INVESTI- 
GATION OF THE ANISOTROPY OF 3S ALUMINUM- 
ALLOY SHEET IN THE PLASTIC RANGE. Arthur J. 
McEvlly, Jr. and Philip J. Hughes. October 1954. 
45p. diagrs., photos., 4 tabs. (NACA TN 3248) 

EXPERIMENTAL INVESTIGATION OF NOTCH -SIZE 
EFFECTS ON ROTATING-BEAM FATIGUE BE- 
HAVIOR OF 75S-T6 ALUMINUM ALLOY. W. S. 
Hyler, R. A. Lewis and H. J. Grover, Battelle 
Memorial Institute. November 1954. 47p. diagrs., 
photos., 12 tabs. (NACA TN 3291) 

INFLUENCE OF EXPOSED AREA ON STRESS- 
CORROSION CRACKING OF 24S ALUMINUM ALLOY. 
William H. Coiner and Howard T. Francis, Armour 
Research Foundation. November 1954. 22p. diagrs., 
photos., tab. (NACA TN 3292) 

INTERGRANULAR CORROSION OF HIGH -PURITY 
ALUMINUM IN HYDROCHLORIC ACID. I -EFFECTS 
OF HEAT TREATMENT, IRON CONTENT, AND 
ACm COMPOSITION. M. Metzger and J. Intrater, 
Columbia University. February 1955. 38p. photos., 
8 tabs. (NACA TN 3281) 

STUDY OF EFFECTS OF MICROSTRUCTURE AND 
ANISOTROPY ON FATIGUE OF 24S-T4 ALUMINUM 
ALLOY. H. A. Lipsitt, G. E. Dieter, G. T. Home 
and R. F. Mehl, Carnegie Institute of Technology. 
March 1955. 41p. diagrs., photos., 4 tabs. (NACA 
TN 3380) 

AN ANALYSIS OF THE STABILITY AND ULTIMATE 
COMPRESSIVE STRENGTH OF SHORT SHEET- 
STRINGER PANELS WITH SPECIAL REFERENCE 
TO THE INFLUENCE OF RIVETED CONNECTION 
BETWEEN SHEET AND STRINGER. Joseph W. 
Semonian and James P. Peterson. March 1955. 
49p. diagrs., tab. (NACA TN 3431) 

INTERGRANULAR CORROSION OF HIGH-PURITY 
ALUMINUM IN HYDROCHLORIC ACID. II - 
GRAIN-BOUNDARY SEGREGATION OF IMPURITY 
ATOMS. M. Metzger and J. Intrater, Columbia 
University. April 1955. 33p. diagrs., 4 tabs. 
(NACA TN 3282) 



PLASTIC DEFORMATION OF ALUMINUM SINGLE 
CRYSTALS AT ELEVATED TEMPERATURES. 
R. D. Johnson, A. P. Yonng and A. D, Schwope, 
Battelle Memorial Institute, April 1955. 76p. 
dlagrs., photos., 3 tabs, (NACA TN 3351) 

SOME OBSEHVATIOI© ON LOSS OF STATIC 
STRENGTH DUE TO FATIGUE CRACIQS, Walter lUg 
and Herbert F. Hardrath. May 1955. 8p, dlagrs. 
(NACA RM L55D15a) 

PRELIMINARY INVESTIGATION OF THE FAILURE 
OF PRESSURIZED STIFFENED CYLINDERS. 
Norris F. Dow and Roger W. Peters. May 1955, 
14p. diagrs., photos., tab. (NACA Mfl L55D15b) 

ANALYSIS OF EAR FORMATION IN DEEP-DRAWN 
CUPS. Arthur J. McEvily, Jr. May 1955. 7p. 
diagrs. (NACA TN 3439) 



STEELS 
(5.1.3) 



TIME -TEMPERATURE PARAMETERS AND AN 
APPLICATION TO RUPTURE AND CREEP OF 
ALUMINUM ALLOYS. George J. Heimerl. June 
1954. 35p. diagrs., tab. (NACA TN 3195) 

HIGH -RESOLUTION AUTORADIOGRAPHY. George 
C. Towe, Henry J. GombergandJ. W. Freeman, 
University of Michigan. July 1954. 11, 138p. 
diagrs., photos., 9 tabs. (NACA TN 3209) 

TENSILE AND COMPRESSIVE STRESS-STRAIN 
PROPERTIES OF SOME HIGH-STRENGTH SHEET 
ALLOYS AT ELEVATED TEMPERATURES. 
Philip J. Hughes, John E. Inge and Stanley B. 
Prosser. November 1954. 32p. diagrs., photos., 
6 tabs. (NACA TN 3315) 



HEAT-RESISTING ALLOYS 
(5.1.4) 



FABRICATION AND PROPERTIES OF HOT- 
PRESSED MOLYBDENUM DISILICIDE. Roger A. 
Long. August 24, 1950. 34p. diagrs., photos., tab. 
(NACA RM E5DF22) 

INVESTIGATION OF MECHANBMS OF BLADE 
FAILURE OF FORGED HASTELLOY B AND CAST 
STELLITE 21 TURBINE BLADES IN TURBOJET 
ENGINE. C. Yaker, C. F. Robards and F. B. 
Garrett. August 1951. 41p. diagrs., photos., 2 tabs. 
(NACARM E51D16) 

SOME FACTORS AFFECTING FABRICATION AND 
HIGH-TEMPERATURE STRENGTH OF MOLYB- 
DENUM DISILICIDE. W. A. Maxwell. April 1952. 
25p. diagrs., photos., 3 tabs. (NACA RM E52B06) 

PRELIMINARY INVESTIGATION OF THE HEAT- 
SHOCK RESISTANT PROPERTIES OF MOLYBDE- 
NUM DISILICIDE BLADES UNDER CENTRIFUGAL 
LOAD. Roger A. Long and John C. Freche. May 
1952. 15p. diagrs., photos., tab. (NACA 
RM E52A17) 



156 



MATERIALS 
TYPES (5. 1) 



Heat-Resisting Alloys (Cont. ) 



SOME STRESS -RUPTURE AND CREEP PROPER- 
TIES OF MOLYBDENUM DISILICIDE IN THE RANGE 
1600° TO 2000° F. W. A. Maxwell. June 1952. 19pi 
diagrs., photos., 2 tabs. (NACA RM E52D09) 

INVESTIGATION OF ENGINE PERFORMANCE AND 
HIGH-TEMPERATURE PROPERTIES OF 
PRECISION-CAST TURBINE BLADES OF HIGH- 
CARBON STELLITE 21 AND CONTROLLED-GRADJ- 
SIZE STELLITE 21. Charles Yaker, Floyd B. 
Garrett and Paul F. Sikora. June 1952. 38p. 
diagrs., photos., 6 tabs. (NACA RM E52D10) 

SURVEY OF PORTIONS OF THE CHROMIUM - 
COBALT-NICKEL-MOLYBDENUM QUATERNARY 
SYSTEM AT 1200° C. Sheldon Paul Rideout and 
Paul A. Beck, University of Notre Dame. 1953 . ii, 
38p. diagrs., photos., 20 tabs. (NACA Rept. 1122. 
Formerly TN 2683) 

BEHAVIOR OF FORGED S-816 TURBINE BLADES 
IN STEADY-STATE OPERATION OF J33-9 TURBO- 
JET ENGINE WITH STRESS-RUPTURE AND 
METALLOGRAPHIC EVALUATIONS. F. B. Garrett, 
C. A. Gyorgak and J. W. Weeton. February 1953. 
29p. diagrs., photos., 3 tabs. (NACA RME52L17) 

ADHESIVE AND PROTECTIVE CHARACTERISTICS 
OF CERAMIC COATING A-417 AND ITS EFFECT 
ON ENGINE LIFE OF FORGED REFRACTALOY-26 
(AMS 5760) AND CAST STELLITE 21 (AMS 5385) 
TURBINE BLADES. Floyd B. Garrett and Charles 
A. Gyorgak. February 1953. 21p. photos., diagr., 
4 tabs. (NACA RM E52L30) 

BEHAVIOR OF MATERIALS UNDER CONDITIONS 
OF THERMAL STRESS. S. S. Manson. 1954. ii, 
34p. diagrs., photos., 6 tabs. (NACA Rept. 1170. 
Formerly TN 2933) 

HIGH -RESOLUTION AUTORADIOGRAPHY. George 
C. Towe, Henry J. Gomberg and J. W. Freeman, 
University of Michigan. July 1954. ii, 138p. 
diagrs., photos., 9 tabs. (NACA TN 3209) 



PRELIMINARY INVESTIGATION OF STRESS- 
RUPTURE AND TENSILE STRENGTH OF 
THERMENOL, AN IRON-ALUMINUM ALLOY. 
Charles A. Gyorgak. August 1954. lip. diagrs., 
3 tabs. (NACA RM E54F10) 



INVESTIGATION OF NICKEL-ALUMINUM ALLOYS 
CONTAINING FROM 14 TO 34 PERCENT ALUMI- 
NUM. W. A. Maxwell and E. M. Grata. August 
1954. 42p. diagrs., photos., 7 tabs. (NACA 
TN 3259) 

A DROP TEST FOR THE EVALUATION OF THE 
IMPACT STRENGTH OF CERMETS. B. Pinkel, 
G. C. Deutsch and N. H. Katz. March 1955. 8p. 
diagrs., photo. (NACA RM E54D13) 



COOPERATIVE INVESTIGATION OF RELATIONSHIP 
BETWEEN STATIC AND FATIGUE PROPERTIES 
OF WROUGHT N-155 ALLOY AT ELEVATED 
TEMPERATURES. NACA Subcommittee on Heat- 
Resisting Materials. April 1955. 92p. diagrs., 
photos., 13 tabs. (NACA TN 3216) 



CERAMICS 
(5.1.5) 



FABRICATION AND PROPERTIES OF HOT- 
PRESSED MOLYBDENUM DISILICIDE. Roger A. 
Long. August 24, 1950. 34p. diagrs., photos., tab. 
(NACA RM E50F22) 

SOME FACTORS AFFECTING FABRICATION AND 
HIGH -TEMPERATURE STRENGTH OF MOLYB- 
DENUM DISILICIDE. W. A. Maxwell. April 1952. 
25p. diagrs., photos., 3 tabs. (NACA RM E52B06) 

PRELIMINARY INVESTIGATION OF THE HEAT- 
SHOCK RESISTANT PROPERTIES OF MOLYBDE- 
NUM DISILICIDE BLADES UNDER CENTRIFUGAL 
LOAD. Roger A. Long and John C. Freche. May 
1952. 15p. diagrs., photos., tab. (NACA 
RM E52A17) 

SOME STRESS-RUPTURE AND CREEP PROPER- 
TIES OF MOLYBDENUM DISILICIDE IN THE RANGE 
1600° TO 2000° F. W. A. Maxwell. June 1952. 19pi 
diagrs., photos., 2 tabs. (NACA RM E52D09) 

ADHESIVE AND PROTECTIVE CHARACTERISTICS 
OF CERAMIC COATING A-417 AND ITS EFFECT 
ON ENGINE LIFE OF FORGED REFRACTALOY-26 
(AMS 5760) AND CAST STELLITE 21 (AMS 5385) 
TURBINE BLADES. Floyd B. Garrett and Charles 
A. Gyorgak. February 1953. 21p. photos., diagr., 
4 tabs. (NACA RM E52L30) 

COMPARISON OF THEORETICALLY AND EXPERI- 
MENTALLY DETERMINED EFFECTS OF OXIDE 
COATINGS SUPPLIED BY FUEL ADDITIVES ON 
UNCOOLED TURBINE-BLADE TEMPERATURE 
DURING TRANSIENT TURBOJET -ENGINE OPERA- 
TION. Louis J. Schafer, Jr., Francis S. Stepka 
and W. Byron Brown. March 1953. 45p. photos., 
diagrs., tab. (NACA RM E53A19) 

RELATION BETWEEN ROUGHNESS OF INTERFACE 
AND ADHERENCE OF PORCELAIN ENAMEL TO 
STEEL. J. C. Richmond, D. G. Moore, H. B. 
Kirkpatrick and W. N. Harrison, National Bureau of 
Standards. 1954. ii, 9p. diagrs., photos., 7 tabs. 
(NACA Rept. 1166. Formerly TN 2934) 

BEHAVIOR OF MATERIALS UNDER CONDITIONS 
OF THERMAL STRESS. S. S. Manson. 1954. ii, 
34p. diagrs., photos., 6 tabs. (NACA Rept. 1170. 
Formerly TN 2933) 

ROLE OF NICKEL DIP IN ENAMELING OF SHEET 
STEEL. D. G. Moore, J. W. Pitts and W. N. 
Harrison, National Bureau of Standards. June 1954. 
27p. diagrs., photos., 8 tabs. (NACA TN 3207) 

A DROP TEST FOR THE EVALUATION OF THE 
IMPACT STRENGTH OF CERMETS. B. Pinkel, 
G. C. Deutsch and N. H. Katz. March 1955. 8p. 
diagrs., photo. (NACA RM E54D13) 

MEASURED EFFECTIVE THERMAL CONDUCTIVITY 
OF URANIUM OXIDE POWDER IN VARIOUS GASES 
AND GAS MIXTURES. J. S. Boegli and R. G. 
Deissler. March 1955. 20p. diagrs., tab. (NACA 
RM E54L10) 



MATERIALS 
TYPES (5. 1) 



157 



PLASTICS 
(5.1.6) 



EFFECTS OF MULTIAXIAL STRETCHING ON CRAZ- 
ING AND OTHER PROPERTIES OF TRANSPARENT 
PLASTICS. Irvln Wolock and Desmond A. George, 
National Bureau of Standards. October 1954. 34p. 
diagrs., photos., 10 tabs. (NACA RM 54F22) 



WOODS 

(5.1.7) 



DESCRIPTION AND INVESTIGATION OF A 
DYNAMIC MODEL OF THE XH-IT TWO-BLADE 
JET -DRIVEN HELICOPTER. George W. Brooks and 
Maurice A. Sylvester. March 14, 1951. 49p. 
diagrs., photos., 6 tabs. (NACA RM L50I21) 



ADHESIVES 
(5.1.8) 



SOME TORSIONAL-DAMPING MEASUREMENTS OF 
LAMINATED BEAMS AS APPLIED TO THE 
PROPELLER STALL-FLUTTER PROBLEM. 
Atwood R. Heath, Jr. April 1953. 14p. diagrs., 
photos., tab. (NACA RM L53A19) 



PROTECTIVE COATINGS 
(5.1.9) 



ADHESIVE AND PROTECTIVE CHARACTERISTICS 
OF CERAMIC COATING A-417 AND ITS EFFECT 
ON ENGINE LIFE OF FORGED REFRACTALOY-26 
(AMS 5760) AND CAST STELLITE 21 (AMS 5385) 
TURBINE BLADES. Floyd B. Garrett and Charles 
A. Gyorgak. February 1953. 21p. photos., diagr., 
4 tabs. (NACA RM E52L30) 



COMPARISON OF THEORETICALLY AND EXPERI- 
MENTALLY DETERMINED EFFECTS OF OXIDE 
COATINGS Sin>PLIED BY FUEL ADDITIVES ON 
UNCOOLED TURBINE-BLADE TEMPERATURE 
DURING TRANSIENT TURBOJET-ENGINE OPERA- 
TION. Louis J. Schafer, Jr., Francis S. Stepka 
and W, Byron Brown. March 1953. 45p. photos., 
diagrs., tab. (NACA RM E53A19) 



RELATION BETWEEN ROUGHNESS OF INTERFACE 
AND ADHERENCE OF PORCELAIN ENAMEL TO 
STEEL. J. C. Richmond, D. G. Moore, H. B. 
Kirkpatrick and W. N. Harrison, National Bureau of 
Standards. 1954. ii, 9p. diagrs., photos., 7 tabs. 
(NACA Rept. 1186. Formerly TN 2934) 



ROLE OF NICKEL DIP IN ENAMELING OF SHEET 
STEEL. D. G. Moore, J. W. Pitts and W. N. 
Harrison, National Bureau of Standards. June 1954. 
27p. diagrs., photos., 8 tabs. (NACA TN 3207) 

EFFECT OF OXYGEN CONTENT OF FURNACE 
ATMOSPHERE ON ADHERENCE OF VITREOUS 
COATINGS TO IRON. A. G. Eubanks and D. G. 
Moore, National Bureau of Standards. May 1955. 
17p. diagrs., photos., 2 tabs. (NACA TN 3297) 



SANDWICH & LAMINATES 
(5.1.11) 



SOME TORSIONAL-DAMPING MEASUREMENTS OF 
LAMINATED BEAMS AS APPLIED TO THE 
PROPELLER STALL-FLUTTER PROBLEM. 
Atwood R. Heath, Jr. April 1953. 14p. diagrs., 
photos., tab. (NACA RM L53A19) 

EFFECTS OF RESIN COATING METHODS AND 
OTHER VARIABLES ON PHYSICAL PROPERTIES 
OF GLASS-FABRIC REINFORCED POLYESTERS. 
B. M. Axilrod, J. E. Wier and J. Mandel, National 
Bureau of Standards. August 1954. 22p., 6 tabs. 
(NACA RM 54G26) 



CERAMALS 
(5.1.12) 



THE DESIGN OF BRITTLE-MATERIAL BLADE 
ROOTS BASED ON THEORY AND RUPTURE TESTS 
OF PLASTIC MODELS. Andre J. Meyer, Jr., 
Albert Kaufman and WiUiam C. Caywood. 
AprUe, 1953. 45p. diagrs., photos., tab. (NACA 
RM E53C12) 

BEHAVIOR OF MATERIALS UNDER CONDITIONS 
OF THERMAL STRESS. S. S. Manson. 1954. ii, 
34p. diagrs., photos., 6 tabs. (NACA Rept. 1170. 
Formerly TN 2933) 

MECHANICAL PROPERTIES AT ROOM TEMPERA- 
TURE OF FOUR CERMETS OF TITANIUM CARBIDE 
WITH NICKEL BINDER. Aldie E. Johnson, Jr. 
August 1954. 22p. diagrs., photos., tabs. (NACA 
TN3197) 

MECHANICAL PROPERTIES AT ROOM TEMPERA- 
TURE OF FOUR CERMETS OF TUNGSTEN CAR- 
BIDE WITH COBALT BINDER. Aldie E. Johnson, 
Jr. December 1954. 16p. diagrs., photo., tab. 
(NACA TN 3309) 

A DROP TEST FOR THE EVALUATION OF THE 
IMPACT STRENGTH OF CERMETS. B. Plnkel, 
G. C. Deutsch and N. H. Katz. March 1955. 8p. 
diagrs., photo. (NACA RM E54D13) 



158 



MATERIALS (5. 2) 



Properties 

(5.2) 



DESCRIPTION AND INVESTIGATION OF A 
DYNAMIC MODEL OF THE XH-17 TWO-BLADE 
JET -DRIVEN HELICOPTER. George W. Brooks and 
Maurice A. Sylvester. March 14, 1951. 49p. 
diagrs., photos.. 6 tabs. (NACA RM L50I21) 

ADHESIVE AND PROTECTIVE CHARACTERISTICS 
OF CERAMIC COATING A-417 AND ITS EFFECT 
ON ENGINE LIFE OF FORGED REFRACTALOY-26 
(AMS 5760) AND CAST STELLITE 21 (AMS 5385) 
TURBINE BLADES. Floyd B. Garrett and Charles 
A. Gyorgak. February 1953. 21p. photos., diagr., 
4 tabs. (NACA RM E52L30) 

BEHAVIOR OF MATERIALS UNDER CONDITIONS 
OF THERMAL STRESS. S. S. Manson. 1954. il, 
34p. diagrs., photos., 6 tabs. (NACA Rept. 1170. 
Formerly TN 2933) 

A FIBROUS-GLASS COMPACT AS A PERMEABLE 
MATERIAL FOR BOUNDARY-LAYER-CONTROL 
APPLICATIONS USING AREA SUCTION. Robert E. 
Dannenberg, James A. Weiberg and Bruno J. 
Gambucci. January 1955. 20p. diagrs., photos., 
2 tabs. (NACA TN 3388) 

A DROP TEST FOR THE EVALUATION OF THE 
IMPACT STRENGTH OF CERMETS. B. Pinkel, 
G. C. Deutsch and N. H. Katz. March 1955. 8p. 
diagrs., photo. (NACA RM E54D13) 



TENSILE 
(5.2.1) 



FABRICATION AND PROPERTIES OF HOT- 
PRESSED MOLYBDENUM DISILICIDE. Roger A. 
Long. August 24, 1950. 34p. diagrs., photos., tab. 
(NACA RM E50F22) 

SOME FACTORS AFFECTING FABRICATION AND 
HIGH-TEMPERATURE STRENGTH OF MOLYB- 
DENUM DISILICIDE. W. A. Maxwell. April 1952. 
25p. diagrs., photos., 3 tabs. (NACA RM E52B06) 



SOME STRESS-RUPTURE AND CREEP PROPER- 
TIES OF MOLYBDENUM DISILICIDE IN THE RANGE 
1600° TO 2000° F. W. A. Maxwell. June 1952. 19p 
diagrs., photos., 2 tabs. (NACA RM E52D09) 

TIME -TEMPERATURE PARAMETERS AND AN 
APPLICATION TO RUPTURE AND CREEP OF 
ALUMINUM ALLOYS. George J. Helmerl. June 
1954. 35p. diagrs., tab. (NACA TN 3195) 

PRELIMINARY INVESTIGATION OF STRESS- 
RUPTURE AND TENSILE STRENGTH OF 
THERMENOL, AN IRON-ALUMINUM ALLOY. 
Charles A. Gyorgak. August 1954. lip. diagrs., 
3 tabs. (NACA RM E54F10) 

MECHANICAL PROPERTIES AT ROOM TEMPERA- 
TURE OF FOUR CERMETS OF TITANIUM CARBIDE 
WITH NICKEL BINDER. Aldie E. Johnson, Jr. 
August 1954. 22p. diagrs., photos., tabs. (NACA 
TN 3197) 



INVESTIGATION OF NICKEL-ALUMINUM ALLOYS 
CONTAINING FROM 14 TO 34 PERCENT ALUMI- 
NUM. W. A. Maxwell and E. M. Grala. August 
1954. 42p. diagrs., photos., 7 tabs. (NACA 
TN 3259) 

EFFECTS OF MULTIAXIAL STRETCHING ON CRAZ- 
ING AND OTHER PROPERTIES OF TRANSPARENT 
PLASTICS. Irvln Wolock and Desmond A. George, 
National Bureau of Standards. October 1954. 34p. 
diagrs., photos., 10 tabs. (NACA RM 54F22) 



AN EXPERIMENTAL AND THEORETICAL INVESTI- 
GATION OF THE ANISOTROPY OF 3S ALUMINUM - 
ALLOY SHEET IN THE PLASTIC RANGE. Arthur J. 
McEvily, Jr. and Philip J. Hughes. October 1954. 
45p. diagrs., photos., 4 tabs. (NACA TN 3248) 



TENSILE AND COMPRESSIVE STRESS-STRAIN 
PROPERTIES OF SOME HIGH-STRENGTH SHEET 
ALLOYS AT ELEVATED TEMPERATURES. 
Philip J. Hughes, John E. Inge and Stanley B. 
Prosser. November 1954. 32p. diagrs., photos., 
6 tabs. (NACA TN 3315) 



MECHANICAL PROPERTIES AT ROOM TEMPERA- 
TURE OF FOUR CERMETS OF TUNGSTEN CAR- 
BIDE WITH COBALT BINDER. Aldie E. Johnson, 
Jr. December 1954. 16p. diagrs., photo., tab. 
(NACA TN 3309) 



THEORY OF REVERSIBLE AND NONREVERSIBLE 
CRACKS IN SOLIDS. (Teoriya obratlmykh i 
neobratimykh treshchin v tverdykh telakh). Y. I. 
Frenkel. April 1955. 14p. diagrs. (NACA 
TM 1387. Trans, from Zhurnal Tekhnicheskoi 
Fiziki, V.22, no. 11, Nov., 1952, p. 1857-1866) 



SOME OBSERVATIONS ON LOSS OF STATIC 
STRENGTH DUE TO FATIGUE CRACKS. Walter lUg 
and Herbert F. Hardrath. May 1955. 8p. diagrs. 
(NACA RM L55D15a) 



COMPRESSIVE 
(5.2.2) 

MECHANICAL PROPERTIES AT ROOM TEMPERA- 
TURE OF FOUR CERMETS OF TITANIUM CARBIDE 
WITH NICKEL BINDER. Aldie E. Johnson, Jr. 
August 1954. 22p. diagrs., photos., tabs. (NACA 
TN 3197) 

AN EXPERIMENTAL AND THEORETICAL INVESTI- 
GATION OF THE ANBOTROPY OF 3S ALUMINUM - 
ALLOY SHEET IN THE PLASTIC RANGE. Arthur J. 
McEvily, Jr. and Philip J. Hughes. October 1954. 
45p. diagrs., photos., 4 tabs. (NACA TN 3248) 



TENSILE AND COMPRESSIVE STRESS-STRAIN 
PROPERTIES OF SOME HIGH -STRENGTH SHEET 
ALLOYS AT ELEVATED TEMPERATURES. 
Philip J. Hughes, John E. Inge and Stanley B. 
Prosser. November 1954. 32p. diagrs., photos., 
6 tabs. (NACA TN 3315) 



MATERIALS 
PROPERTIES (5.2) 



159 



Compressive (Cont. ) 



MECHANICAL PROPERTIES AT ROOM TEMPERA- 
TURE OF FOXJR CERMETS OF TUNGSTEN CAR- 
BIDE WITH COBALT BINDER. Aldie E. Johnson, 
Jr. December 1954. 16p. diagrs., photo., tab. 
(NACA TN 3309) 



CREEP 
(5.2.3) 



SOME STRESS-RUPTURE AND CREEP PROPER- 
TIES OF MOLYBDENUM DISILICIDE IN THE RANGE 
1600° TO 2000° F. W. A. Maxwell. June 1952. lOpi 
diagrs., photos., 2 tabs. (NACA RM E52D09) 

INVESTIGATION OF ENGINE PERFORMANCE AND 
HIGH-TEMPERATURE PROPERTIES OF 
PRECISION-CAST TURBINE BLADES OF HIGH- 
CARBON STELLITE 21 AND CONTROL LED -GRAIN - 
SIZE STELLITE 21. Charles Yaker, Floyd B. 
Garrett and Paul F. Slkora. June 1952. 38p. 
diagrs., photos., 6 tabs. (NACA RM E52D10) 

TIME -TEMPERATURE PARAMETERS AND AN 
APPLICATION TO RUPTURE AND CREEP OF 
ALUMINUM ALLOYS. George J. Heimerl. June 
1954. 35p. diagrs., tab. (NACA TN 3195) 

AN INVESTIGATION OF THE CREEP LIFETIME OF 
75S-T6 ALUMINUM -ALLOY COLUMNS. Eldon E. 
Mathauser and William A. Brooks, Jr. July 1954. 
28d. d'agrs., photos., tab. (NACA TN 3204) 

INVESTIGATIOlJ OF NICKEL-ALUMINUM ALLOYS 
CONTAINING FROM 14 TO 34 PERCENT ALUMI- 
NUM. W. A. Maxwell and E. M. Grala. August 
1954. 42p. diagrs., photos., 7 tabs. (NACA 
TN 3259) 

INVESTIGATION OF STATIC STRENGTH AND 
CREEP BEHAVIOR OF AN ALUMINUM -ALLOY 
MULTIWEB BOX BEAM AT ELEVATED TEMPER- 
ATURES. Eldon E. Mathauser. November 1954. 
21p. diagrs., photos., 4 tabs. (NACA TN 33 10) 

PLASTIC DEFORMATION OF ALUMINUM SINGLE 
CRYSTALS AT ELEVATED TEMPERATURES. 
R. D. Johnson, A. P. Young and A. D. Schwope, 
Battelle Memorial Institute. April 1955. 76p. 
diagrs., photos., 3 tabs. (NACA TN 3351) 



STRESS-RUPTURE 
(5.2.4) 



SOME STRESS-RUPTURE AND CREEP PROPER- 
TIES OF MOLYBDENUM DISILICIDE IN THE RANGE 
1600° TO 2000° F. W. A. Maxwell. June 1952. 19p 
diagrs., photos., 2 tabs. (NACA RM E52D09) 



INVESTIGATION OF ENGINE PERFORMANCE AND 
HIGH-TEMPERATURE PROPERTIES OF 
PRECISION-CAST TURBINE BLADES OF HIGH- 
CARBON STELLITE 21 AND CONTROL LED -GRAIN - 
SIZE STELLITE 21. Charles Yaker, Floyd B. 
Garrett and Paul F. Sikora. June 1952. 38p. 
diagrs., photos., 6 tabs. (NACA RM E52D10) 



BEHAVIOR OF FORGED S-816 TURBINE BLADES 
IN STEADY-STATE OPERATION OF J33-9 TURBO- 
JET ENGINE WITH STRESS-RUPTURE AND 
METALLOGRAPHIC EVALUATIONS. F. B. Garrett, 
C. A. Gyorgak and J. W. Weeton. February 1953. 
29p. diagrs., photos., 3 tabs. (NACA RM E52L17) 



TIME -TEMPERATURE PARAMETERS AND AN 
APPLICATION TO RUPTURE AND CREEP OF 
ALUMINUM ALLOYS. George J. Heimerl. June 
1954. 35p. diagrs., tab. (NACA TN 3195) 



PRELIMINARY INVESTIGATION OF STRESS- 
RUPTURE AND TENSILE STRENGTH OF 
THERMENOL, AN IRON-ALUMINUM ALLOY. 
Charles A. Gyorgak. August 1954. lip. diagrs., 
3 tabs. (NACA RM E54F10) 

INVESTIGATION OF NICKEL-ALUMINUM ALLOYS 
CONTAINING FROM 14 TO 34 PERCENT ALUMI- 
NUM. W. A. Maxwell and E. M. Grala. August 
1954. 42p. diagrs., photos., 7 tabs. (NACA 
TN 3259) 

COOPERATIVE INVESTIGATION OF RELATIONSHIP 
BETWEEN STATIC AND FATIGUE PROPERTIES 
OF WROUGHT N-155 ALLOY AT ELEVATED 
TEMPERATURES. NACA Subcommittee on Heat- 
Resisting Materials. April 1955. 92p. diagrs., 
photos., 13 tabs. (NACA TN 3216) 



FATIGUE 
(5.2.5) 



ADDITIONAL STATIC AND FATIGUE TESTS OF 
HIGH-STRENGTH ALUMINUM-ALLOY BOLTED 
JOINTS. E. C. Hartmann, Marshall Holt and I. D. 
Eaton, Aluminum Company of America. July 1954. 
42p. diagrs., photos., 7 tabs. (NACA TN 3269) 

EXPERIMENTAL INVESTIGATION OF NOTCH -SIZE 
EFFECTS ON ROTATING-BEAM FATIGUE BE- 
HAVIOR OF 75S-T6 ALUMINUM ALLOY. W. S. 
Hyler, R. A. Lewis and H. J. Grover, Battelle 
Memorial Institute. November 1954. 47p. diagrs., 
photos., 12 tabs. (NACA TN 3291) 

STUDY OF EFFECTS OF MICROSTRUCTURE AND 
ANISOTROPY ON FATIGUE OF 24S-T4 ALUMINUM 
ALLOY. H. A. Llpsitt, G. E. Dieter, G. T. Home 
and R. F. Mehl, Carnegie Institute of Technology. 
March 1955. 41p. diagrs., photos., 4 tabs. (NACA 
TN 3380) 

COOPERATIVE INVESTIGATION OF RELATIONSHIP 
BETWEEN STATIC AND FATIGUE PROPERTIES 
OF WROUGHT N-155 ALLOY AT ELEVATED 
TEMPERATURES. NACA Subcommittee on Heat- 
Resisting Materials. April 1955. 92p. diagrs., 
photos., 13 tabs. (NACA TN 3216) 



SOME OBSERVATIOira ON LOSS OF STATIC 
STRENGTH DUE TO FATIGUE CRACKS. Walter Ulg 
and Herbert F. Hardrath. May 1955. 8p. diagrs. 
(NACA RM L55D15a) 



PRELIMINARY INVESTIGATION OF THE FAILURE 
OF PRESSURIZED STIFFENED CYLINDERS. 
Norris F. Dow and Roger W. Peters. May 1955. 
14p. diagrs., photos., tab. (NACA RM L55D15b) 



MATERIALS 
160 PROPERTIES (5. 2) 



SHEAR 
(5.2.6) 



MECHANICAL PROPERTIES AT ROOM TEMPERA- 
TURE OF FOUR CERMETS OF TITANIUM CARBIDE 
WITH NICKEL BINDER. Aldie E. Johnson, Jr. 
August 1954. 22p. diagrs., photos., tabs. (NACA 
TN3197) 

MECHANICAL PROPERTIES AT ROOM TEMPERA- 
TURE OF FOUR CERMETS OF TUNGSTEN CAR- 
BIDE WITH COBALT BINDER. Aldie E. Johnson, 
Jr. December 1954. 16p. diagrs., photo., tab. 
(NACA TN 3309) 

PRELIMINARY INVESTIGATION OF PROPERTIES 
OF HIGH-TEMPERATURE BRAZED JOINTS PRO- 
CESSED IN VACUUM OR IN MOLTEN SALT. C. A. 
Gyorgak and A. C. Francisco. May 1955. 29p. 
diagrs., photos., 7 tabs. (NACA TN 3450) 



FLEXURAL 
(5.2.7) 



EFFECTS OF RESIN COATING METHODS AND 
OTHER VARIABLES ON PHYSICAL PROPERTIES 
OF GLASS-FABRIC REINFORCED POLYESTERS. 
B. M. Axilrod, J. E. Wier and J. Mandel, National 
Bureau of Standards. August 1954. 22p., 6 tabs. 
(NACA RM 54G26) 

COOPERATIVE INVESTIGATION OF RELATIONSHIP 
BETWEEN STATIC AND FATIGUE PROPERTIES 
OF WROUGHT N-155 ALLOY AT ELEVATED 
TEMPERATURES. NACA Subcommittee on Heat- 
Reslsting Materials. April 1955. 92p. diagrs., 
photos., 13 tabs. (NACA TN 3216) 



CORROSION RESISTANCE 
(5.2.8) 



ROLE OF NICKEL DIP IN ENAMELING OF SHEET 
STEEL. D. G. Moore, J. W. Pitts and W. N. 
Harrison, National Bureau of Standards. June 1954. 
27p. diagrs., photos., 8 tabs. (NACA TN 3207) 



EFFECTS OF ADDITIVES ON CORROSION AND 
MASS TRANSFER IN SODIUM HYDROXIDE - 
NICKEL SYSTEMS UNDER FREE -CONVECTION 
CONDITIONS. Americo F. Forestieri. August 1954. 
13p. diagrs., photos., 6 tabs. (NACA RM E54E19) 

INVESTIGATION OF NICKEL-ALUMINUM ALLOYS 
CONTAINING FROM 14 TO 34 PERCENT ALUMI- 
NUM. W. A. Maxwell and E. M. Grala. August 
1954. 42p. diagrs., photos., 7 tabs. (NACA 
TN 3259) 

INFLUENCE OF EXPOSED AREA ON STRESS- 
CORROSION CRACKING OF 24S ALUMINUM ALLOY. 
William H. Coiner and Howard T. Francis, Armour 
Research Foundation. November 1954. 22p. diagrs., 
photos., tab. (NACA TN 3292) 



CORROSION OF METALS OF CONSTRUCTION BY 
ALTERNATE EXPOSURE TO LIQUID AND 
GASEOUS FLUORINE. Richard M. Gundzlk and 
Charles E. Feiler. December 1954. lOp. photos., 
3 tabs. (NACA TN 3333) 

INTERGRANULAR CORROSION OF HIGH-PURITY 
ALUMINUM IN HYDROCHLORIC ACID. I - EFFECTS 
OF HEAT TREATMENT, IRON CONTENT, AND 
ACID COMPOSITION. M. Metzger and J. Intrater, 
Columbia University. February 1955. 38p. photos., 
8 tabs. (NACA TN 3281) 



INTERGRANULAR CORROSION OF HIGH-PUKn)( 
ALUMINUM IN HYDROCHLORIC ACID. II - 
GRAIN-BOUNDARY SEGREGATION OF IMPURITY 
ATOMS. M. Metzger and J. Intrater, Columbia 
University. April 1955. 33p. diagrs., 4 tabs. 
(NACA TN 3282) 



STRUCTURE 
(5.2.9) 



CORRELATION OF SUPERSONIC CONVECTIVE 
HEAT -TRANSFER COEFFICIENTS FROM MEAS- 
UREMENTS OF THE SKIN TEMPERATURE OF A 
PARABOLIC BODY OF REVOLUTION (NACA RM-10). 
Leo T. Chauvin and Carlos A. deMoraes. March 7, 
1951. 39p. diagrs., photo. 2 tabs. (NACA 
RM L51A18) 



SURVEY OF PORTIONS OF THE CHROMIUM- 
COBALT-NICKEL-MOLYBDENUM QUATERNARY 
SYSTEM AT 1200° C. Sheldon Paul Hideout and 
Paul A. Beck, University of Notre Dame. 1953. ii, 
38p. diagrs., photos., 20 tabs. (NACA Rept. 1122. 
Formerly TN 2683) 



HIGH -RESOLUTION AUTORADIOGRAPHY. George 
C. Towe, Henry J. Gomberg and J. W. Freeman, 
University of Michigan. July 1954. ii, 138p. 
diagrs., photos., 9 tabs. (NACA TN 3209) 



AN EXPERIMENTAL AND THEORETICAL INVESTI- 
GATION OF THE ANISOTROPY OF 3S ALUMINUM- 
ALLOY SHEET IN THE PLASTIC RANGE. Arthur J. 
McEvily, Jr. and Philip J. Hughes. October 1954. 
45p. diagrs., photos., 4 tabs. (NACA TN 3248) 



THEORY OF REVERSIBLE AND NONREVERSIBLE 
CRACKS IN SOLIDS. (Teoriya obratimykh i 
neobratimykh treshchin v tverdykh telakh). Y. I. 
Frenkel. April 1955. 14p. diagrs. (NACA 
TM 1387. Trans, from Zhurnal Tekhnicheskoi 
Fiziki, v. 22, no. 11, Nov., 1952, p. 1857-1866) 



ANALYSIS OF EAR FORMATION IN DEEP-DRAWN 
Cin>S. Arthur J. McEvily, Jr. May 1955. 7p. 
diagrs. (NACA TN 3439) 



PRELIMINARY INVESTIGATION OF PROPERTIES 
OF Hiai-TEMPERATURE BRAZED JOINTS PRO- 
CESSED IN VACUUM OR IN MOLTEN SALT. C. A. 
Gyorgak and A. C. Francisco. May 1955. 29p. 
diagrs., photos., 7 tabs. (NACA TN 3450) 



MATERIALS 
PROPERTIES (5. 2) 



161 



THERMAL 
(5.2.11) 



PRELIMINARY INVESTIGATION OF THE HEAT- 
SHOCK RESISTANT PROPERTIES OF MOLYBDE- 
NUM DISILICIDE BLADES UNDER CENTRIFUGAL 
LOAD. Roger A. Long and John C. Freche. May 
1952. 15p. diagrs., photos., tab. (NACA 
RM E52A17) 

SURVEY OF PORTIONS OF THE CHROMIUM- 
COBALT-NICKEL-MOLYBDENUM QUATERNARY 
SYSTEM AT 1200° C. Sheldon Paul Hideout and 
Paul A. Beck, University of Notre Dame. 1953. ii, 
38p. diagrs., photos., 20 tabs. (NACA Rept. 1122. 
Formerly TN 2683) 

AN INVESTIGATION OF THE CREEP LIFETIME OF 
75S-T6 ALUMINUM -ALLOY COLUMNS. Eldon E. 
Mathauser and William A. Brooks, Jr. July 1954. 
28p. diagrs., photos., tab. (NACATN 3204) 

SOME EFFECTS OF EXPOSURE TO EXHAUST -GAS 
STREAMS ON EMITTANCE AND THERMOELECTRIC 
POWER OF BARE-WIRE PLATINUM RHODIUM - 
PLATINUM THERMOCOUPLES. George E. Glawe 
and Charles E. Shepard. August 1954. 30p. diagrs., 
photos. (NACA TN 3253) 

INVESTIGATION OF STATIC STRENGTH AND 
CREEP BEHAVIOR OF AN ALUMINUM -ALLOY 
MULTIWEB BOX BEAM AT ELEVATED TEMPER- 
ATURES. Eldon E. Mathauser. November 1954. 
21p. diagrs., photos., 4 tabs. (NACA TN 3310) 

MEASURED EFFECTIVE THERMAL CONDUCTIVITY 
OF URANIUM OXIDE POWDER IN VARIOUS GASES 
AND GAS MIXTURES. J. S. Boegli and R. G. 
Deissler. March 1955. 20p. diagrs., tab. (NACA 
RM E54L10) 

PLASTIC DEFORMATION OF ALUMINUM SINGLE 
CRYSTALS AT ELEVATED TEMPERATURES. 
R. D. Johnson, A. P. Young and A. D. Schwope, 
Battelle Memorial Institute. April 1955. 76p. 
diagrs., photos., 3 tabs. (NACA TN 3351) 



EFFECT OF PRESSURE ON THERMAL CONDUC- 
TANCE OF CONTACT JOINTS. Martin E. 
Barzelay, Kin Nee Tong and George F. Holloway, 
Syracuse University. May 1955. 52p. diagrs., 
2 tabs. (NACA TN 3295) 



MULTIAXIAL STRESS 
(5.2.12) 



COOPERATIVE INVESTIGATION OF RELATIONSHIP 
BETWEEN STATIC AND FATIGUE PROPERTIES 
OF WROUGHT N-155 ALLOY AT ELEVATED 
TEMPERATURES. NACA Subcommittee on Heat- 
Resisting Materials. April 1955. 92p. diagrs., 
photos., 13 tabs. (NACA TN 3216) 



PLASTICITY 
(5.2.13) 



AN EXPERIMENTAL AND THEORETICAL INVESTI- 
GATION OF THE ANISOTROPY OF 3S ALUMINUM- 
ALLOY SHEET IN THE PLASTIC RANGE. Arthur J. 
McEvily, Jr. and Philip J. Hughes. October 1954. 
45p. diagrs., photos., 4 tabs. (NACA TN 3248) 



PLASTIC DEFORMATION OF ALUMINUM SINGLE 
CRYSTALS AT ELEVATED TEMPERATURES. 
R. D. Johnson, A. P. Young and A. D. Schwope, 
Battelle Memorial Institute. April 1955. 76p. 
diagrs., photos., 3 tabs. (NACA TN 3351) 



ANALYSIS OF EAR FORMATION IN DEEP-DRAWN 
CUPS. Arthur J. McEvily, Jr. May 1955. 7p. 
diagrs. (NACA TN 3439) 



162 MATERIALS 



Operating Stresses and Conditions 



(5.3) 



THE DESIGN OF BRITTLE-MATERIAL BLADE 
ROOTS BASED ON THEORY AND RUPTURE TESTS 
OF PLASTIC MODELS. Andre J. Meyer, Jr., 
Albert Kaufman and William C. Caywood. 
April 6, 1953. 45p. diagrs., photos., tab. (NACA 
RM E53C12) 



METEOROLOGY 
(6) 




METEOROLOGY 163 



METEOROLOGY 

(6) 



VARIATION OF LOCAL LIQUID-WATER CONCEN- 
TRATION ABOUT AN ELLIPSOID OF FINENESS 
RATIO 5 MOVING IN A DROPLET FIELD. Robert 
G. Dorsch and Rinaldo J. Brun. July 1954. 68p. 
diagrs., photos., 2 tabs. (NACA TN 3153) 



KINETIC TREATMENT OF THE NUCLEATION IN 
SUPERSATURATED VAPORS. (Kinetische 
Behandlung der Keimbildung in ubersattigten 
Dampfen). R. Becker and W. Doring. September 
1954. 43p. diagrs. (NACA TM 1374. Trans, from 
Annalen der Physlk, Ser. 5, v. 24, 1935, p. 719-752), 



VARIATION OF LOCAL LIQUID-WATER CONCEN- 
TRATION ABOUT AN ELLIPSOID OF FINENESS 
RATIO 10 MOVING IN A DROPLET FIELD. Rinaldo 
J. Brun and Robert G. Dorsch. April 1955. 51p. 
diagrs., photo., tab. (NACA TN 3410) 



164 METEOROLOGY 



Atmosphere 
(6.1) 



A DYE -TRACER TECHNIQUE FOR EXPERIMENTAL- 
LY OBTAINING IMPINGEMENT CHARACTERISTICS 
OF ARBITRARY BODIES AND A METHOD FOR 
DETERMINING DROPLET SIZE DISTRIBUTION. 
Uwe H. von Glahn, Thomas F. Gelder and William H. 
Smyers, Jr. March 1955. 73p. diagrs., photos., 
tab. (NACA TN 3338) 



GUSTS 
(6.1.2) 



A STUDY OF THE APPLICATION OF POWER- 
SPECTRAL METHODS OF GENERAUZED HARMON- 
IC ANALYSIS TO GUST LOADS ON AIRPLANES. 
Harry Press and Bernard Mazelsky. 1954. 11, 17p. 
diagrs., 2 tabs. (NACA Rept. 1172. Formerly 
TN 2853) 

AN INVESTIGATION OF THE USE OF ROCKET- 
POWERED MODELS FOR GUST -LOAD STUDIES 
WITH AN APPLICATION TO A TAILLESS SWEPT- 
WING MODEL AT TRANSONIC SPEEDS. A. James 
Vitale, H. Press and C. C. ShuHlebarger. June 
1954. 36p. diagrs., photos., tab. (NACA TN 3161) 

GUST-LOAD AND, AIRSPEED DATA FROM ONE 
TYPE OF FOUR-ENGINE AIRPLANE ON FIVE 
ROUTES FROM 1947 TO 1954. Walter G. Walker. 
January 1955. 28p. diagrs., 4 tabs. (NACA 
TN 3358) 

ANALYSIS OF ACCELERATIONS, GUST VELOCI- 
TIES, AND AIRSPEEDS FROM OPERATIONS OF A 
TWIN-ENGINE TRANSPORT AIRPLANE ON A 
TRANSCONTINENTAL ROUTE FROM 1950 TO 1952. 
Thomas L. Coleman and Walter G. Walker. 
February 1955. 16p. diagrs., 3 tabs. (NACA 
TN 3371) 

AN ANALYSIS OF ACCELERATIONS, AIRSPEEDS, 
AND GUST VELOCITIES FROM THREE COMMER- 
CIAL OPERATIONS OF ONE TYPE OF MEDIUM- 
ALTITUDE TRANSPORT AIRPLANE. Thomas L. 
Coleman, Martin R. Copp, Walter G. Walker and 
Jerome N. Engel. March 1955. 31p. diagrs., 
4 tabs. (NACA TN 3365) 



STRUCTURE 
(6.1.2.1) 



INVESTIGATION OF MACH NUMBER CHANGES 
OBTAINED BY DISCHARGING HIGH-PRESSURE 
PULSE THROUGH WIND TUNNEL OPERATING 
SUPERSONICALLY. Rudolph C. Haefeli and Harry 
Bernstein. August 1954. 14p. diagrs., photos., 
tab. (NACA TN 3258) 



TURBULENCE 
(6. 1.2.3) 

SOME MEASUREMENTS OF ATMOSPHERIC 
TURBULENCE OBTAINED FROM FLOW-DIRECTION 
VANES MOUNTED ON AN AIRPLANE. Robert G. 
Chilton. November 1954. 22p. diagrs., photo., 
tab. (NACA TN 3313) 

ESTIMATES OF PROBABILITY DISTRIBUTION OF 
ROOT -MEAN-SQUARE GUST VELOCITY OF 
ATMOSPHERIC TURBULENCE FROM OPERATION- 
AL GUST -LOAD DATA BY RANDOM-PROCESS 
THEORY. Harry Press, May T. Meadows and Ivan 
Hadlock. March 1955. 48p. diagrs., 4 tabs. 
(NACA TN 3362) 

SOME CALCULATIONS OF THE LATERAL RE- 
SPONSE OF TWO AIRPLANES TO ATMOSPHERIC 
TURBULENCE WITH RELATION TO THE LATERAL 
SNAKING PROBLEM. John D. Bird. May 1955. 
24p. diagrs., 2 tabs. (NACA TN 3425. Formerly 
RM L50F26a) 



ALLEVIATION 
(6.1.2.4) 

A COMPARISON OF GUST LOADS MEASURED IN 
FLIGHT ON A SWEPT -WING AIRPLANE AND AU 
UNSWEPT-WING AIRPLANE. Jack Funk and 
Harry C. Mickleboro. June 1953. 16p. diagrs., 
2 tabs. (NACA RM L52L02) 



METEOROLOGY 



165 



Ice Formation 
(6.2) 



IMPINGEMENT OF WATER DROPLETS ON WEDGES 
AND DOUBLE -WEDGE AIRFOILS AT SUPERSONIC 
SPEEDS. Johns. Serafinl. 1954. 11, 24p. dlagrs. 
(NACA Rept. 1159. Formerly TN 29711 



A PROCEDURE FOR THE DESIGN OF AIR-HEATED 
ICE -PREVENTION SYSTEMS. Carr B. Neel, Jr. 
June 1954. 63p. diagrs., photo. (NACA TN 3130) 



VARIATION OF LOCAL LIQUID-WATER CONCEN- 
TRATION ABOUT AN ELLIPSOID OF FINENESS 
RATIO 5 MOVING IN A DROPLET FIELD. Robert 
G. Dorsch and Rlnaldo J. Brun. July 1954. 68p. 
diagrs., photos., 2 tabs. (NACA TN 3153) 



IMPINGEMENT OF WATER DROPLETS ON NACA 
65A004 AIRFOIL AT 8° ANGLE OF ATTACK. 
Rlnaldo J. Brun, Helen M. Gallagher and Dorothea 
E. Vogt. July 1954. 27p. diagrs. (NACA TN 3155) 



A HEATED-WIRE LIQUID-WATER-CONTENT 
INSTRUMENT AND RESULTS OF INITIAL FLIGHT 
TESTS IN ICING CONDITIONS. Carr B. Neel. 
January 1955. 33p. diagrs., photos., tab. (NACA 
RM A54I23) 



INGESTION OF FOREIGN OBJECTS INTO TURBINE 
ENGINES BY VORTICES. Lewis A. Rodert and 
Floyd B. Garrett. February 1955. 23p. diagrs., 
photos. (NACA TN 3330) 



ICING LIMIT AND WET -SURFACE TEMPERATURE 
VARIATION FOR TWO AIRFOIL SHAPES UNDER 
SIMULATED HIGH-SPEED FLIGHT CONDITIONS. 
Willard D. Coles. February 1955. 33p. diagrs., 
photos. (NACA TN 3396) 



A DYE-TRACER TECHNIQUE FOR EXPERIMENTAL- 
LY OBTAINING IMPINGEMENT CHARACTERISTICS 
OF ARBITRARY BODIES AND A METHOD FOR 
DETERMINING DROPLET SIZE DISTRIBUTION. 
Uwe H. von Glahn, Thomas F. Gelder and William H. 
Smyers, Jr. March 1955. 73p. diagrs., photos., 
tab. (NACA TN 3338) 



VARIATION OF LOCAL UQUID-WATER CONCEN- 
TRATION ABOUT AN ELLIPSOID OF FINENESS 
RATIO 10 MOVING IN A DROPLET FIELD. Rlnaldo 
J. Brun and Robert G. Dorsch. April 1955. 51p. 
diagrs., photo., tab. (NACA TN 3410) 



OPERATING PROBLEMS 

(7) 




OPERATING PROBLEMS 167 



OPERATING PROBLEMS 

(7) 



DROP HAMMER TESTS WITH THREE OLEO STRUT 
MODELS AND THREE DIFFERENT SHOCK STRUT 
OILS AT LOW TEMPERATURES. (Fallhammer- 
versuche mit drei OUederstrebenmustern und drei 
verschiedenen Federstrebenolen bei tlefen 
Temperaturen). Kranz. July 1954. 55p. diagrs., 
photos., 10 tabs. (NACA TM 1372. Trans, from 
Zentrale fiir wissenschaftliches Berichtswesen der 
Luftfahrtforschung, Berlin, UM 564, Jan. 17, 1939) 



GUST-LOAD AND AIRSPEED DATA FROM ONE 
TYPE OF FOUR-ENGINE AIRPLANE ON FIVE 
ROUTES FROM 1947 TO 1954. Walter G. Walker. 
January 1955. 28p. diagrs., 4 tabs. (NACA 
TN 3358) 



ANALYSIS OF ACCELERATIONS, GUST VELOCI- 
TIES, AND AIRSPEEDS FROM OPERATIONS OF A 
TWIN-ENGINE TRANSPORT AIRPLANE ON A 
TRANSCONTINENTAL ROUTE FROM 1950 TO 1952. 
Thomas L. Coleman and Walter G. Walker. 
February 1955. 16p. diagrs., 3 tabs. (NACA 
TN 3371) 



AN INVESTIGATION OF DRAINS DISCHARGING 
LIQUID INTO SUBSONIC AND TRANSONIC STREAMS. 
Allen R. Vick and Frank V. Silhan. March 1955. 
54p. diagrs., photos., tab. (NACA TN 3359) 



AN ANALYSE OF ACCELERATIONS, AIRSPEEDS, 
AND GUST VELOCITIES FROM THREE COMMER- 
CUL OPERATIONS OF ONE TYPE OF MEDIUM - 
ALTITUDE TRAiePORT AIRPLANE. Thomas L. 
Coleman, Martin R. Copp, Walter G. Walker and 
Jerome N. Engel. March 1955. 31p. diagrs., 
4Ubs. (NACA TN 3365) 



INVESTIGATION OF JET-ENGINE NOISE REDUC- 
TION BY SCREENS LOCATED TRANSVERSELY 
ACROSS THE JET. Edmund E. Callaghan and 
Willard D. Coles. May 1955. 27p. diagrs., photos., 
tab. (NACA TN 3452) 



168 OPERATING PROBLEMS 



Safety 
(7.1) 



FLIGHT INVESTIGATION OF THE JETTISONABLE- 
NOSE METHOD OF PILOT ESCAPE USING ROCKET- 
PROPELLED MODELS. Reginald R. Lundstrom and 
Burke R. O'Kelly. June 2, 1949. 27p. diagrs., 
photos., 2 tabs. (NACA EM L9Dn) 

AN INVESTIGATION OF THE SPIN, RECOVERY. 
AND TUMBLING CHARACTERISTICS OF A 1/20- 
SCALE MODEL OF THE NORTHROP X-4 AIRPLANE. 
Lawrence J. Gale, Ira P. Jones, Jr. and Jack H. 
Wilson. January 4, 1950. 27p. diagrs., photos., 4 
tabs. (NACA RM L9K28) 

SPIN-TUNNEL INVESTIGATION OF A MODEL OF 
A 60° DELTA -WING AIRPLANE TO DETERMINE 
THE SPIN, RECOVERY, AND LONGITUDINAL 
TRIM CHARACTERISTICS THROUGHOUT AN 
EXTENSIVE RANGE OF MASS LOADINGS. Walter 
J. Kllnar and Ira P. Jones, Jr. February 15, 1950. 
56p. diagrs. , photos. , 6 charts, 4 tabs. 
(NACA RM L9L06) 

THE PATH AND MOTION OF SCALE MODELS OF 
JETTISONABLE NOSE SECTIONS AT SUPERSONIC 
SPEEDS AS DETERMINED FROM AN INVESTIGA- 
TION IN THE LANGLEY FREE -FLIGHT APPARA- 
TUS. Lawrence J. Gale. May 23, 1950. 35p. 
diagrs., photos., 2 tabs. (NACA RM L9J13a) 

SPIN AND RECOVERY CHARACTERISTICS OF A 
MODEL OF A FIGHTER TYPE OF AIRPLANE WITH- 
OUT A HORIZONTAL TAIL AND HAVING EITHER A 
SINGLE VERTICAL TAIL OR TWIN VERTICAL 
TAILS. Lawrence J. Gale and Norman E. 
Pumphrey. July 25, 1950. 23p. diagrs., photos., 
2 tabs. (NACA*RM L50F19a) 

SURVEY OF LESS-INFLAMMABLE HYDRAULIC 
FLUIDS FOR AIRCRAFT. Wray V. Drake and 
I. L. Drell. September 7, 1950. 64p. 14 tabs. 
(NACA RM E50F29) 

SPIN-TUNNEL INVESTIGATION OF A MODEL OF 
A SWEPT-WDJG FIGHTER AIRPLANE OVER A 
WIDE RANGE OF FUSELAGE -HEAVY LOADINGS. 
Theodore Herman. December 27, 1950. 51p. 
diagrs., photos., 2 tabs. (NACA RM L50L08) 

STATIC LONGITUDINAL STABILITY AND 
DYNAMIC CHARACTERISTICS AT HIGH ANGLES 
OF ATTACK AND AT LOW REYNOLDS NUMBERS 
OF A MCXJEL OF THE X-3 SUPERSONIC RESEARCH 
AIRPLANE. Sanger M. Burk, Jr. and Burton E. 
Hultz. February 6, 1951. 76p. diagrs., photos., 
4 tabs. (NACA RM L50L19) 

EFFECT OF CURRENT DESIGN TRENDS ON AIR- 
PLANE SPINS AND RECOVERIES. Anshal L 
Neihouse. January 1952. 6p. diagrs. (NACA RM 
L52A09) 

MECHANISM OF START AND DEVELOPMENT OF 
AIRCRAFT CRASH FIRES. L Irving Plnkel, G. 
Merritt Preston and Gerald J. Pesman. 1953. iii, 
52p. diagrs., photos., 2 tabs. (NACA Rept. 1133. 
Formerly RM E52F06) 



WIND-TUNNEL INVESTIGATION OF THE BE- 
HAVIOR OF PARACHUTES IN CLOSE PROXIMITY 
TO ONE ANOTHER. Stanley H. Scher. August 
1953. 12p. photos. (NACA RM L53G07) 

ANALYTICAL DETERMINATION OF THE 
MECHANISM OF AN AIRPLANE SPIN RECOVERY 
WITH DIFFERENT APPLIED YAWING MOMENTS 
BY USE OF ROTARY-BALANCE DATA. Sanger M. 
Burk, Jr. December 1954. 43p. diagrs., 2 tabs. 
(NACA TN 3321) 

PRELIMINARY INVESTIGATION OF A STICK 
SHAKER AS A LIFT -MARGIN INDICATOR. James 
P. Trant, Jr. February 1955. 19p. diagrs., 
photos. (NACA TN 3355) 

CIRCUMFERENTIAL DISTRIBUTION OF 
PROPELLER-SLIPSTREAM TOTAL -PRESSURE 
RISE AT ONE RADIAL STATION OF A TWIN- 
ENGINE TRANSPORT AIRPLANE. A. W. Vogeley 
and H. A. Hart. April 1955. 24p. diagrs., photos. 
(NACA TN 3432) 



PILOT-ESCAPE TECHNIQUES 



(7.1.1) 



SUMMARY OF RESULTS OF TUMBUNG INVESTI- 
GATIONS MADE IN THE LANGLEY 2t)-FOOT FREE- 
SPINNING TUNNEL ON 14 DYNAMIC MODELS. 
Ralph W. Stone, Jr. and Robert L. Bryant. 
December 31, 1948. 91p. diagrs., photos., 23 tabs. 
(NACA RM L8J28) 

AN EMPIRICAL CRITERION FOR FIN STABI- 
LIZING JETTISONABLE NOSE SECTIONS OF AIR- 
PLANES. Stanley H. Scher. December 8, 1949. 
21p. diagrs., photo., tab. (NACA RM L9I28) 

WIND-TUNNEL INVESTIGATION AT LOW SPEED 
TO DETERMINE AERODYNAMIC PROPERTIES OF 
A JETTISONABLE NOSE SECTION WITH CIRCULAR 
CROSS SECTION. Roscoe H. Goodwin. May 19, 

1950. 38p. diagrs., photos. (NACA RM L9J13) 

MOTION OF A TRANSONIC AIRPLANE NOSE SEC- 
TION WHEN JETTISONED AS DETERMINED FROM 
WIND-TUNNEL INVESTIGATIONS ON A 1/25-SCALE 
MODEL. Stanley H. Scher and Lawrence J. Gale. 
May 26, 1950. 64p. diagrs., photos., tab. (NACA 
RM L9L08a) 

THE CALCULATION OF THE PATH OF A JETTI- 
SONABLE NOSE SECTION. Roscoe H. Goodwin. 
September 7, 1950. 35p. diagrs. (NACA RM L50G18) 

ESTIMATED DECELERATION OF AIRPLANE NOSE 
SECTION JETTISONED AT VAWOUS ALTITUDfeS 
AND AIRSPEEDS. Stanley H. Scher. January 8, 

1951. 39p. diagrs. (NACA RM L50K09) 



OPERATING PROBLEMS 169 



Ice Prevention and Removal 



(7.3) 



ICING LIMIT AND WET -SURFACE TEMPERATURE 
VARIATION FOR TWO AIRFOIL SHAPES UNDER 
SIMULATED HIGH-SPEED FLIGHT CONDITIONS. 
Wlllard D. Coles. February 1955. 33p. diagrs., 
photos. (NACATN3396) 

A DYE -TRACER TECHNIQUE FOR EXPERIMENTAL- 
LY OBTAINING IMPINGEMENT CHARACTERISTICS 
OF ARBITRARY BODIES AND A METHOD FOR 
DETERMINING DROPLET SIZE DISTRIBUTION. 
Uwe H. von Glahn, Thomas F. Gelder and William H. 
Smyers, Jr. March 1955. 73p. diagrs., photos., 
tab. (NACA TN 3338) 



PROPELLERS 
(7.3.2) 



A PROCEDURE FOR THE DESIGN OF AIR -HEATED 
ICE -PREVENTION SYSTEMS. Carr B. Neel, Jr. 
June 1954. 63p. diagrs., photo. (NACA TN 3130) 

IMPINGEMENT OF WATER DROPLETS ON NACA 
65A004 AIRFOIL AT 8° ANGLE OF ATTACK. 
Rlnaldo J. Brun, Helen M. Gallagher and Dorothea 
E. Vogt. July 1954. 27p. diagrs. (NACA TN 3155) 



WINGS AND TAILS 



(7.3.3) 



IMPINGEMENT OF WATER DROPLETS ON WEDGES 
AND DOUBLE -WEDGE AIRFOIIS AT SUPERSONIC 
SPEEDS. Johns. Seraflni. 1954. 11, 2^. diagrs. 
(NACA Rept. 1159. Formerly TN 2971) 

A PROCEDIffiE FOR THE DESIGN OF AIR-HEATED 
ICE -PREVENTION SYSTEMS. Carr B. Neel, Jr 
June 1954. 63p. diagrs., photo. (NACA TN 3130) 

IMPINGEMENT OF WATER DROPLETS ON NACA 
65A004 AIRFOIL AT 8° ANGLE OF ATTACK. 
Rinaldo J. Brun, Helen M. Gallagher and Dorothea 
E. Vogt. July 1954. 27p. diagrs. (NACA TN 3155) 

ICING LIMIT AND WET -SURFACE TEMPERATURE 
VARIATION FOR TWO AIRFOIL SHAPES UNDER 
SIMULATED HIGH-SPEED FLIGHT CONDITIONS. 
Willard D. Coles. February 1955. 33p. diagrs., 
photos. (NACA TN 3396) 



WINDSHIELDS 
(7.3.4) 

A PROCEDURE FOR THE DESIGIJ OF AIR -HEATED 
ICE -PREVENTION SYSTEMS. Carr B. Neel, Jr. 
June 1954. 63p. diagrs., photo. (NACA TN 3130) 

MISCELLANEOUS 

ACCESSORIES 

(7.3.5) 

A PROCEDURE FOR THE DESIGN OF AIR -HEATED 
ICE-PREVENTION SYSTEMS. Carr B. Neel, Jr.. 
June 1954. 63p. diagrs., photo. (NACA TN 3130) 

VARIATION OF LOCAL LIQUID-WATER CONCEN- 
TRATION ABOUT AN ELLIPSOID OF FINENESS 
RATIO 5 MOVING IN A DROPLET FIELD. Robert 
G. Dorsch and Rinaldo J. Brun. July 1954. 6Bp. 
diagrs., photos.,. 2 tabs. (NACA TN 3153) 

VARIATION OF LOCAL LIQUTO-WATER CONCEN- 
TRATION ABOUT AN ELLIPSOID OF FINENESS 
RATIO 10 MOVING IN A DROPLET FIELD. Rinaldo 
J. Brun and Robert G. Dorsch. April 1955. 51p. 
diagrs., photo., tab. (NACA TN 3410) 

PROPULSION SYSTEMS 



(7.3.6) 



INVESTIGATION OF POWER REQUIREMENTS FOR 
ICE PREVENTION AND CYCUCAL DE-ICING OF 
INLET GUIDE VANES WITH INTERNAL ELECTRIC 
HEATERS. Uwe von Glahn and Robert E. Blatz. 
December 1, 1950. 49p. diagrs., photos. (NACA 
RM E50H29) 

ICING CHARACTERISTICS AND ANTI-ICING HEAT 
REQUIREMENTS FOR HOLLOW AND INTERNALLY 
MODIFIED GAS-HEATED DJLET GUIDE VANES. 
Vernon H. Gray and Dean T. Bowden. December 5, 
1950. 49p. diagrs., photos. (NACA RM E50I08) 

INGESTION OF FOREIGN OBJECTS INTO TURBINE 
ENGINES BY VORTICES. Lewis A. Rodert and 
Floyd B. Garrett. February 1955. 23p. diagrs., 
photos. (NACA TN 3330) . 



170 OPERATING PROBLEMS 



Noise 
(7.4) 



EXPERIMENTS TO DETERMINE NEIGHBORHOOD 
REACTIONS TO LIGHT AIRPLANES WITH AND 
WITHOUT EXTERNAL NOISE REDUCTION. Fred S. 
Elwell, Aeronautical Research Foundation. 1953. 
it, 43p. dlagrs., photos., 12 tabs. (NACA Rept. 1156. 
Formerly TN 2728) 



THE NEAR NOISE FIELD OF STATIC JETS AND 
SOME MODEL STUDIES OF DEVICES FOR NOISE 
REDUCTION. Leslie W. Lassiter apd Harvey H. 
Hubbard. July 1954. 38p. diagrs., photos. (NACA 
TN 3187) 



OSCILLATING PRESSURES NEAR A STATIC 
PUSHER PROPELLER AT TIP MACH NUMBERS UP 
TO 1.20 WITH SPECIAL REFERENCE TO THE EF- 
FECTS OF THE PRESENCE OF THE WING. Harvey 
H. Hubbard and Leslie W. Lassiter. July 1954. 
35p. diagrs., photos., tab. (NACA TN 3202) 



SHOCK-TURBULENCE INTERACTION AND THE 
GENERATION OF NOISE. H. S. Ribner. July 1954. 
60p. diagrs., tab. (NACA TN 3255) 



SOME ASPECTS OF THE HELICOPTER NOISE 
PROBLEM. Harvey H. Hubbard and Leslie W. 
Lassiter. August 1954. 14p. diagrs., photo. 
(NACA TN 3239) 



INVESTIGATION OF NOISE FIELD AND VELOCITY 
PROFILES OF AN AFTERBURNING ENGINE. 
Warren J. North, Edmund E. Callahan and Chester 
D. Lanzo. September 1954. 23p. diagrs., photos. 
(NACA RM E54G07) 

TRANSVERSE OSCILLATIONS IN A CYLINDRICAL 
COMBUSTION CHAMBER. Franklin K. Moore and 
Stephen H. Maslen. October 1954. 25p. diagrs. 
(NACA TN 3152) 

SOME MEASUREMENTS OF NOISE FROM THREE 
SOLID-FUEL ROCKET ENGINES. Leslie W. 
Lassiter and Robert H. Heitkotter. December 1954. 
21p. diagrs. (NACA TN 3316) 

A SURVEY OF BACKGROUND AND AIRCRAFT 
NOISE IN COMMUNITIES NEAR AIRPORTS. K. N. 
Stevens, Bolt Beranek and Newman, Inc. December 
1954. 36p. diagrs., tab. (NACA TN 3379) 

MEASUREMENTS OF FREE -SPACE OSCILLATING 
PRESSURES NEAR A PROPELLER AT FLIGHT 
MACH NUMBERS TO 0.72. Arthur W. Vogeley and 
Max C. Kurbjun. May 1955. 24p. diagrs., photos., 
tab. (NACA TN 3417) 

itqVESTIGATION OF JET-ENGINE NOISE REDUC- 
TION BY SCREENS LOCATED TRANSVERSELY 
ACROSS THE JET. Edmimd E. Calla^ian and 
Wlllard D. Coles. May 1955. 27p. diagrs., photos., 
tab. (NACA TN 3452) 



OPERATING PROBLEMS 171 



Piloting Techniques 

{7.7) 



MEASXJHED CHARACTERISTICS OF THE DOUGLAS 
D-558-1 AIRPLANE (BUAERO NO. 37971) IN TWO 
LANDINGS. Hubert M. Drake. June 3, 1949. 8p. 
diagrs., photos. (NACA RM L9D20a) 



AN INVESTIGATION OF THE SPIN, RECOVERY, 
AND TUMBLING CHARACTERISTICS OF A 1/20- 
SCALE MODEL OF THE NORTHROP X-4 AIRPLANE. 
Lawrence J. Gale, Ira P. Jones, Jr. and Jack H. 
Wilson. January 4, 1950. 27p. diagrs., photos., 4 
tabs. (NACA RM L9K28) 

SPIN AND RECOVERY CHARACTERISTICS OF A 
MODEL OF A FIGHTER TYPE OF AIRPLANE WITH- 
OUT A HORIZONTAL TAIL AND HAVING EITHER A 
SINGLE VERTICAL TAIL OR TWIN VERTICAL 
TAILS. Lawrence J. Gale and Nornr.an E. 
Pumphrey. July 25, 1950. 23p. diagrs., photos., 
2 tabs. (NACA RM L50F19a) 



SPIN-TUNNEL INVESTIGATION OF A MODEL OF 
A SWEPT-WING FIGHTER AIRPLANE OVER A 
WIDE RAKGE OF FUSELAGE-HEAVY LOADINGS. 
Theodore Berman. December 27, 1950. 51p. 
diagrs., photos., 2 tabs. (NACA RM L50L08) 

EFFECT OF CURRENT DESIGN TRENDS ON AIR- 
PLANE SPINS AND RECOVERIES. Anshal I. 
Neihouse. January 1952. 6p. diagrs. (NACA RM 
L52A091 

PRELIMINARY INVESTIGATION OF A STICK 
SHAKER AS A LIFT -MARGIN INDICATOR. James 
P. Trant, Jr. February 1955. 19p. diagrs., 
photos. (NACA TN 3355) 

GROUND-SIMULATOR STUDY OF THE EFFECTS 
OF STICK FORCE AND DISPLACEMENT ON 
TRACKING PERFORMANCE. Stanley Faber. 
April 1955. 21p. diagrs., photos. (NACA TN 3428) 



172 OPERATING PROBLEMS 



Physiological 
(7.8) 



AN EMPIRICAL CRITERION FOR FIN STABI- 
LIZING JETTISONABLE NOSE SECTIONS OF AIR- 
PLANES. Stanley H. Scher. December 8, 1949. 
21p. dlagrs., photo., tab. (NACA RM L9I28) 

MOTION OF A TRANSONIC AIRPLANE NOSE SEC- 
TION WHEN JETTISONED AS DETERMINED FROM 
WIND-TUNNEL INVESTIGATIONS ON A 1/25-SCALE 
MODEL. Stanley H. Scher and Lawrence J. Gale. 
May 26, 1950. 64p. dlagrs., photos., tab. (NACA 
RM L9L08a) 



ESTIMATED DECELERATION OF AIRPLANE NOSE 
SECTION JETTISONED AT VARIOUS ALTITUDES 
AND AIRSPEEDS. Stanley H. Scher. January 8, 
1951. 39p. dlagrs. (NACA RM L50K09) 



OPERATING PROBLEMS 173 



Fire Hazards 
(7.9) 



SURVEY OF LESS-INFLAMMABLE HYDRAULIC 
FLUIDS FOR AIRCRAFT. Wray V. Drake and 
I. L. Drell. September 7, 1950. 64p. 14 tabs. 
(NACA RM E50F29) 



MECHANISM OF START AND DEVELOPMENT OF 
AIRCRAFT CRASH FIRES. I. Irving Pinkel, G. 
Merritt Preston and Gerald J. Pesman. 1953. iii, 
52p. diagrs., photos., 2 tabs. (NACA Rept. 1133. 
Formerly RM E52F06) 



174 OPERATING PROBLEMS 



General 
(7.10) 



FUGHT INVESTIGATION OF THE EFFECT OF 
SIDESUP ON THE PRESSURE AT THE STATIC 
ORIFICES OF THE BCffiING B-29 AIRPLANE. Robert 
G. Chilton and B. Porter Brown. AprU 11, 1951. 12p. 
dlagrs. (NACA RM L50J30) 

EXPERIMENTS TO DETERJJINE NEIGHBORHOOD 
REACTIOfB TO LIGHT AIRPLANES WITH AND 
WITHOUT EXTERNAL NOISE REDUCTION. Fred S. 
Elwell, Aeronautical Research Foundation. 1953. 
il, 43p. diagrs., photos., 12 tabs. (NACA Rept. 1156. 
Formerly TN 2728) 



INGESTION OF FOREIGN OBJECTS INTO TURBINE 
ENGINES BY VORTICES. Lewis A. Rodert and 
Floyd B. Garrett. February 1955. 23p. diagrs., 
photos. (NACA TN 3330) 



INSTRUMENTS 
(8) 




INSTRUMENTS 175 



INSTRUMENTS 

(8) 



DETERMINATION OF FLAME TEMPERATURES 
FROM 2000° TO 3000° K BY MICROWAVE ABSORP- 
TION. Perry W. Kuhns. August 1954. 48p. 
diagrs.,. photo., 2 tabs. (NACA TN 3254) 



176 INSTRUMENTS 



Flight 
(8.1) 



THE STATIC-PRESSURE ERROR OF WING AND 
FUSELAGE AIRSPEED INSTALLATIONS OF THE X-1 
AIRPLANES IN TRANSONIC FLIGHT. Harold R. 
Goodman and Roxanah B. Yancey. July 22, 1949. 
20p. diagrs. (NACA RM L9G22) 

FLIGHT CALIBRATION OF FOUR AIRSPEED 
SYSTEMS ON A SWEPT -WING AIRPLANE AT 
MACE NUMBERS UP TO 1.04 BY THE NACA 
RADAR-PHOTOTHEODOLITE METHOD. Jim 
Rogers Thompson, Richard S. Bray and George E. 
Cooper. October 27, 1950. 41p. diagrs., photos., 
tab. (NACA RM A50H24) 

ERROR IN AIRSPEED MEASUREMENT DUE TO 
STATIC -PRESSURE FIELD AHEAD OF THE WING 
TIP OF A SWEPT -WING AIRPLANE MODEL AT 
TRANSONIC SPEEDS. Edward C. B. Danforth and 
Thomas C. O'Bryan. March 1, 1951. 16p. diagrs., 
photo. (NACA RM L50L28) 

SKIN-TEMPERATURE TELEMETER FOR 
DETERMINING BOUNDARY-LAYER HEAT- 
TRANSFER COEFFICIENTS. CliKord L. Fricke 
and Francis B. Smith. March 15, 1951. 22p. 
diagrs. (NACA RM L50J17) 

FLIGHT INVESTIGATION OF THE EFFECT OF 
SIDESLIP ON THE PRESSURE AT THE STATIC 
ORIFICES OF THE BCffiING B-29 AIRPLANE. Robert 
G. Chilton and B. Porter Brown. April 11, 1951. 12p. 
diagrs. (NACA RM L50J30) 

WIND-TUNNEL INVESTIGATION OF A SHIELDED 
TOTAL-PRESSURE TUBE AT TRANSONIC SPEEDS. 
William Gracey, Albin O. Pearson and Walter R. 
Russell. January 1952. 8p. diagrs. (NACA 
RM L51K19) 

ERROR IN AIRSPEED MEASUREMENT DUE TO 
STATIC-PRESSURE FIELD AHEAD OF AN OPEN- 
NOSE AIR -INLET MODEL AT TRANSONIC SPEEDS. 
Thomas C. O'Bryan. March 1952. 17p. diagrs., 
photos. (NACA RM L52A17) 

CALIBRATION OF A CCMBINED PITOT -STATIC 
TUBE AND VANE-TYPE FLOW ANGULARITY IN- 
DICATOR AT TRANSONIC SPEEDS AND AT LARGE 
ANGLES OF ATTACK OR YAW. Albin O. Pearson 
and Harold A. Brown. September 1952. 25p. 
diagrs., photos. (NACA RM L52F24) 

A METHOD OF CALIBRATING AIRSPEED INSTAL- 
LATIONS ON AIRPLANES AT TRANSONIC AND 
SUPERSONIC SPEEDS BY THE USE OF ACCEL- 
EROMETER AND ATTITUDE-ANGLE MEASURE- 
MENTS. John A. Zalovcik, Lindsay J. Llna and 
James P. Trant, Jr. 1953. 11, 13p. diagrs., 
photos., tab. (NACA Rept. 1145. Formerly 
TN 2099; TN 2570) 

VARIATION OF LOCAL LIQUID-WATER CONCEN- 
TRATION ABOUT AN ELLIPSOID OF FINENESS 
RATIO 5 MOVING IN A DROPLET FIELD. Robert 
G. Dorsch and Rlnaldo J. Brun. July 1954. 68p. 
diagrs., photos., 2 tabs. (NACA TN 3153) 



THEORETICAL INVESTIGATION AT SUBSONIC 
SPEEDS OF THE FLOW AHEAD OF A SLENDER 
INCLINED PARABOLIC -ARC BODY OF REVOLU- 
TION AND CORRELATION WITH EXPERIMENTAL 
DATA OBTAINED AT LOW SPEEDS. WiUiara Letko 
and Edward C. B. Danforth, III. July 1954. 56p. 
diagrs. (NACA TN 3205) 



RECOVERY CORRECTIONS FOR BUTT -WELDED, 
STRAIGHT-WIRE THERMOCOUPLES IN HIGH- 
VELOCITY, HIGH-TEMPERATURE GAS STREAMS. 
Frederick S. Simmons. September 1954. 19p. 
diagrs. (NACA RM E54G22a) 



DESCRIPTION AND PRELIMINARY FLIGHT INVES- 
TIGATION OF AN INSTRUMENT FOR DETECTING 
SUBNORMAL ACCELERATION DURING TAKE-OFF. 
Garland J. Morris and Lindsay J. Lina. Novenr.ber 
1954. 19p. diagrs., photos. (NACA TN 3252) 



A HEATED-WIRE LIQUID-WATER-CONTENT 
INSTRUMENT AND RESULTS OF INITIAL FLIGHT 
TESTS IN ICING CONDITIONS. Carr B. Neel. 
January 1955. 33p. diagrs., photos., tab. (NACA 
RM A54I23) 

PRELIMINARY INVESTIGATION OF A STICK 
SHAKER AS A LIFT -MARGIN INDICATOR. James 
P. Trant, Jr. February 1955. 19p. diagrs., 
photos. (NACA TN 3355) 



TWO MINIATURE TEMPERATURE RECORDERS 
FOR FLIGHT USE. John V. Foster. April 1955. 
13p. diagrs., photos. (NACA TN 3392) 

VARIATION OF LOCAL LIQUID-WATER CONCEN- 
TRATION ABOUT AN ELLIPSOID OF FINENESS 
RATIO 10 MOVING IN A DROPLET FIELD. Rlnaldo 
J. Brun and Robert G. Dorsch. April 1955. 51p. 
diagrs., photo., tab. (NACA TN 3410) 



CIRCUMFERENTIAL DISTRIBUTION OF 
PROPELLER-SLIPSTREAM TOTAL-PRESSURE 
RISE AT ONE RADIAL STATION OF A TWIN- 
ENGINE TRANSPORT AIRPLANE. A. W. Vogeley 
and H. A. Hart. April 1955. 24p. diagrs., photos. 
(NACA TN 3432) 



MEASUREMENTS OF FREE -SPACE OSCILLATING 
PRESSURES NEAR A PROPELLER AT FLIGHT 
MACH NUMBERS TO 0.72. Arthur W. Vogeley and 
Max C. Kurbjun. May 1955. 24p. diagrs., photos., 
tab. (NACA TN 3417) 



AN NACA VANE -TYPE ANGLE -OF-ATTACK IN- 
DICATOR FOR USE AT SUBSONIC AND SUPERSONIC 
SPEEDS. Jesse L. Mitchell and Robert F. Peck. 
May 1955. 8p. diagrs., photo. (NACA TN 3441. 
Formerly RM L9F28a) 



INSTRUMENTS 



177 



Laboratory 

(8.2) 



INSTRUMENTATION FOR RECORDING TRANSIENT 
PERFORMANCE OF GAS-TURBINE ENGINES AND 
CONTROL SYSTEMS. Gene J. Delio and Glennon V. 
Schwent. June 27, 1951. 27p. dlagrs., photos. 
(NACA RM E51D27) 

SOME EFFECTS OF EXPOSURE TO EXHAUST -GAS 
STREAMS ON EMITTANCE AND THERMOELECTRIC 
POWER OF BARE-WIRE PLATINUM RHODIUM - 
PLATINUM THERMOCOUPLES. George E. Glawe 
and Charles E. Shepard. August 1954. 30p. diagrs., 
photos. (NACA TN 3253) 

RECOVERY CORRECTIONS FOR BUTT -WELDED, 
STRAIGHT -WIRE THERMOCOUPLES IN HIGH- 
VELOCITY, HIGH-TEMPERATURE GAS STREAMS. 
Frederick S. Simmons. September 1954. 19p. 
diagrs. (NACA RM E54G22a) 

SHEARING-STRESS MEASUREMENTS BY USE OF A 
HEATED ELEMENT. H. W. Liepmann and G. T. 
Skinner, California Institute of Technology. 
November 1954. 27p. diagrs. (NACA TN 3268) 



USE OF A HOT-WIRE ANEMOMETER IN SHOCK- 
TUBE INVESTIGATIONS. Darshan Singh Dosanjh, 
Johns Hopkins University. December 1954. 11, 98p. 
diagrs., photos. (NACA TN 3163) 



A SELF-EXCITED, ALTERNATING-CURRENT, 
CONSTANT -TEMPERATURE HOT-WIRE ANEMOM- 
ETER. Charles E. Shepard. April 1955. 29p. 
diagrs., photos. (NACA TN 3406) 



ANALYTIC DETERMINATION OF THE DISCHARGE 
COEFFICIENTS OF FLOW NOZZLES. Frederick S. 
Simmons. April 1955. 15p. diagrs. (NACA 
TN 3447) 



HEAT -LOSS CHARACTERISTICS OF HOT-WIRE 
ANEMOMETERS AT VARIOUS DENSITIES IN 
TRANSONIC AND SUPERSONIC FLOW. W. G. 
Spangenberg, National Bureau of Standards. May 
1955. 82p. diagrs., photos., 14 tabs. (NACA 
TN 3381) 



178 INSTRUMENTS 



Meteorological 

(8.3) 



VARIATION OF LOCAL LIQUID-WATER CONCEN- 
TRATION ABOUT AN ELLIPSOID OF FINENESS 
RATIO 5 MOVING IN A DROPLET FIELD. Robert 
G. Dorsch and Rlnaldo J. Brun. July 1954. 68p. 
diagrs., photos., 2 tabs. (NACATN31533 

A HEATED-WIRE LIQUID-WATER-CONTENT 
INSTRUMENT AND RESULTS OF INITIAL FLIGHT 
TESTS IN ICING CONDITIONS. Carr B. Neel. 
January 1955. 33p. diagrs., photos., tab. (NACA 
RM A54I23) 



VARIATION OF LOCAL UQUID-WATER CONCEN- 
TRATION ABOUT AN ELLIPSOID OF FINENESS 
RATIO 10 MOVING IN A DROPLET FIELD. Rinaldo 
J. Brun and Robert G. Dorsch. April 1955. 51p. 
diagrs., photo., tab. (NACA TN 3410) 



RESEARCH EQUIPMENT 
AND TECHNIQUES 

(9) 




RESEARCH EQUIPMENT AND TECHNIQUES 179 

RESEARCH EQUIPMENT 

and TECHNIQUES 
(9) 



APPLICATIONS OF AUXILIARY AIR INJECTORS TO 
SUPERSONIC WIND TUNNELS. Joseph M. Spiegel, 
Robert U. Hofstetter and Donald M. Kuehn. 
November 1953. 53p. diagrs., photos. (NACA 
RM A53I01) 

DETERMINATION OF FLAME TEMPERATURES 
FROM 2000° TO 3000° K BY MICROWAVE ABSORP- 
TION. Perry W. Kuhns. August 1954. 48p. 
diagrs., photo., 2 tabs. (NACA TN 3254) 



STARTING AND OPERATING LIMITS OF TWO 
SUPERSONIC WIND TUNNELS UTILIZING AUXIL- 
IARY AIR 0JJECTION DOWNSTREAM OF THE 
TEST SECTION. Henry R. Hunczak and Morris D. 
Rousso. September 1954. 28p. diagrs., photo. 
(NACA TN 3262) 

USE OF A HOT-WIRE ANEMOMETER IN SHOCK- 
TUBE INVESTIGATIONS. Darshan Singh Dosanjh, 
Johns Hopkins University. December 1954. ii, 98p. 
diagrs., photos. (NACA TN 3163) 



180 RESEARCH EQUIPMENT AND TECHNIQUES 



Equipment 
(9.1) 



DIRECT MEASUREMENTS OF SKIN FRICTION. 
Satish Dhawan, California Institute of Technology. 
1953. il, 20p. diagrs., photos. (NACA Rept. 1121. 
Formerly TN 2567) 

APPLICATIONS OF AUXILIARY AIR INJECTORS TO 
SUPERSONIC WIND TUNNELS. Joseph M. Spiegel, 
Robert U. Hofstetter and Donald M. Kuehn. 
November 1953. 53p. diagrs., photos. (NACA 
RM A53I01) 

CONSIDERATIONS ON A LARGE HYDRAULIC JET 
CATAPULT. Upshur T. Joyner and Walter B. 
Home. July 1954. 49p. diagrs., photos., tab. 
(NACA TN 3203. Formerly RM L51B27) 

AN EVALUATION OF AN ACCELEROMETER 
METHOD FOR OBTAINING LANDING-GEAR DRAG 
LOADS. Jerome G. Theisen and Philip M. Edge, Jr. 
October 1954. 22p. diagrs., photos. (NACA 
TN 3247) 

SHEARING-STRESS MEASUREMENTS BY USE OF A 
HEATED ELEMENT. H. W. Liepmann and G. T. 
Skinner, California Institute of Technology, 
November 1954. 27p. diagrs. (NACA TN 3268) 

SOME MEASUREMENTS OF ATMOSPHERIC 
TURBULENCE OBTAINED FROM FLOW -DIRECTION 
VANES MOUNTED ON AN AIRPLANE. Robert G. 
Chilton. November 1954. 22p. diagrs., photo., 
tab. (NACA TN 3313) 

FLIGHT TESTING BY RADIO REMOTE CONTROL - 
FLIGHT EVALUATION OF A BEEP-CONTROL 
SYSTEM. Howard L. Turner, John S. White and 
Rudolph D. Van Dyke, Jr. March 1955. 55p. 
diagrs., photos., tab. (NACA TN 3496. Formerly 
RM A52A29) 

DESIGN AND PERFORMANCE OF THROTTLE- 
TYPE FUEL CONTROLS FOR ENGINE DYNAMIC 
STUDIES. Edward W. Otto, Harold Gold and Kirby 
W. HiUer. April 1955. 39p. diagrs., photo. 
(NACA TN 3445) 



WIND TUNNELS 



(9.1.1) 



AN 8-FOOT AXISYMMETRICAL FIXED NOZZLE 
FOR SUBSONIC MACH NUMBERS UP TO 0.99 AND 
FOR A SUPERSONIC MACH NUMBER OF 1.2. 
Virgil S. Ritchie, Ray H. Wright and Marshall P. 
Tuiin. February 23, 1950. 52p. diagrs., photos., 
2 tabs. (NACA RM L50A03a) 

INVESTIGATION OF PERFORATED CONVERGENT- 
DIVERGENT DIFFUSERS WITH miTIAL BOUNDARY 
LAYER. Maynard I. Weinstein. August 15, 1950. 
26p. diagrs., photo. (NACA RM E50F12) 

AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBER OF 1.38 OF FOUR WrNGS OF ASPECT 
RATIO 4 HAVING QUARTER-CHORD SWEEP 
ANGLES OF 0°, 35°, 45°, AND 60°. WUIiam B. 
Kemp, Jr., Kenneth W. Goodson and Robert A. Booth. 
October 10, 1950. 41p. diagrs., photos., tab. 
(NACA RM L50G14) 



APPARATUS FOR OBTAINING A SUPERSONIC 
FLOW OF VERY SHORT DURATION AND SOME 
DRAG MEASUREMENTS OBTAINED WITH ITS USE. 
John E. Yeates, Jr. , F. J. Bailey, Jr. and T. J. 
Voglewede. July 23, 1951. 23p. diagrs., photos. 
(NACA RM L9C01) 

EFFECT OF THICKNESS, CAMBER, AND THICK- 
NESS DISTRIBUTION ON AIRFOIL CHARACTERIS- 
TICS AT MACH NUMBERS UP TO 1.0. Bernard N. 
Daley and Richard S. Dick. October 1952. 76p. 
photos., diagrs., tab. (NACA RM'L52G31a) 

CONSIDERATIONS ON THE EFFECT OF WIND- 
TUNNEL WALLS ON OSCILLATING AIR FORCES 
FOR TWO-DIMENSIONAL SUBSONIC COMPRES- 
SIBLE FLOW. Harry L. Runyan and Charles E. 
Watkins. 1953. 11, 7p. diagrs. (NACA Rept. 1150. 
Formerly TN 2552) 

APPLICATIONS OF AUXILIARY AIR INJECTORS TO 
SUPERSONIC WIND TUNNELS. Joseph M. Spiegel, 
Robert U. Hofstetter and Donald M. Kuehn. 
November 1953. 53p. diagrs., photos. (NACA 
RM A53I01) 

THE ZERO -LIFT DRAG OF A SLENDER BODY OF 
REVOLUTION (NACA RM-10 RESEARCH MODEL) 
AS DETERMINED FROM TESTS IN SEVERAL WIND 
TUNNELS AND IN FLIGHT AT SUPERSONIC 
SPEEDS. Albert J. Evans. 1954. ii, 13p. 
diagrs. , tab. (NACA Rept. 1160. Formerly 
TN 2944) 

CONVECTION OF A PATTERN OF VORTICITY 
THROUGH A SHOCK WAVE. H. S. Ribner. 1954. 
ii, 17p. diagrs. (NACA Rept. 1164. Formerly 
TN 2864) 

AN ANALYSIS OF SHOCK-WAVE CANCELLATION 
AND REFLECTION FOR POROUS WALLS WHICH 
OBEY AN EXPONENTIAL MASS-FLOW PRESSURE- 
DIFFERENCE RELATION. Joseph M. Spiegel and 
Phillips J. Tunnell. August 1954. 23p. diagrs. 
(NACA TN 3223) 

SOME POSSIBILITIES OF USING GAS MIXTURES 
OTHER THAN AIR IN AERODYNAMIC RESEARCH. 
Dean R. Chapman. August 1954. 48p. diagrs., 4 
tabs. (NACA TN 3226) 

INVESTIGATION OF MACH NUMBER CHANGES 
OBTAINED BY DISCHARGING HIGH -PRESSURE 
PULSE THROUGH WIND TUNNEL OPERATING 
SUPEHSONICALLY. Rudolph C. Haefeli and Harry 
Bernstein. August 1954. 14p. diagrs., photos., 
tab. (NACA TN 3258) 

KINETIC TREATMENT OF THE NUCLEATION IN 
SUPERSATURATED VAPORS. (Kinetlsche 
Behandlung der Keimbildung in ubersattigten 
Dampfen). R. Becker and W. During. September 
1954. 43p. diagrs. (NACA TM 1374. Trans, from 
Annalen der Physik, Ser. 5, v. 24, 1935, p. 719-752). 

STARTING AND OPERATING LIMITS OF TWO 
SUPERSONIC WIND TUNNELS UTILIZING AUXIL- 
IARY AIR INJECTION DOWNSTREAM OF THE 
TEST SECTION. Henry R. Hunczak and Morris D. 
Rousso. September 1954. 28p. diagrs., photo. 
(NACA TN 3262) 



RESEARCH EQUIPMENT AND TECHNIQUES 

EQUIPMENT (9. 1) 



181 



Wind Tunnels (Cont. ) | 

INVESTIGATION OF LIFT, DRAG, AND PITCHING 
MOMENT OF A 60O DELTA-WING— BODY COM- 
BINATION (AGARD CALIBRATION MODEL B) IN 
THE LANGLEY 9-INCH SUPERSONIC TUNNEL. 
August F. Bromm, Jr. September 1954. 18p. 
diagrs., photos. (NACA TN 3300) 

LIQUEFACTION OF AIR IN THE LANGLEY 11-INCH 
HYPERSONIC TUNNEL. Charles H. McLellan and 
Thomas W. Williams. October 1954. 36p. diagrs., 
4 tabs. (NACA TN 3302) 

AN ACCURATE AND RAPID METHOD FOR THE 
DESIGN OF SUPERSONIC NOZZLES. Ivan E. 
Beckwith and John A. Moore. February 1955. 
57p. diagrs., 3 tabs. (NACA TN 3322) 

FREE-FLIGHT 
(9.1.2) 

FLIGHT INVESTIGATION OF THE JETTISONABLE- 
NOSE METHOD OF PILOT ESCAPE USING ROCKET- 
PROPELLED MODELS. Reginald R. Lundstrom and 
Burke R. O'KeUy. June 2, 1949. 27p. diagrs., 
photos., 2 tabs. (NACA RM L9D11) 

FLIGHT CALIBRATION OF FOUR AIRSPEED 
SYSTEMS ON A SWEPT -WING AIRPLANE AT 
MACH NUMBERS UP TO 1.04 BY THE NACA 
HADAR-PHOTOTHEODOLirE METHOD. Jim 
Rogers Thompson, Richard S. Bray and George E. 
Cooper. October 27, 1950. 41p. diagrs., photos., 
tab. (NACA RM A50H24) 

A COMPARISON OF TWO TECHNIQUES UTILIZING 
ROCKET -PROPELLED VEHICLES FOR THE DE- 
TERMINATION OF THE DAMPING-IN-ROLL 
DERIVATIVE. David G. Stone and Carl A. Sandahl. 
May 3, 1951. 17p. diagrs., photos. (NACA 
RM L51A16) 

WIND-TUNNEL INVESTIGATION OF A SHIELDED 
TOTAL-PRESSURE TUBE AT TRANSONIC SPEEDS. 
William Gracey, Albin O. Pearson and Walter R. 
Russell. January 1952. 8p. diagrs. (NACA 
RM L51K19) 

A PRELIMINARY INVESTIGATION OF SHOCK-WAVE 
REFLECTIONS IN A SMALL CLOSED BALLISTIC 
RANGE WITH VARIOUS TYPES OF WALLS. A. P. 
Sabol. September 1952. 21p. photos., diagrs. 
(NACA RM L52G25) 

A METHOD OF CALIBRATING AIRSPEED INSTAL- 
LATIONS ON AIRPLANES AT TRANSONIC AND 
SUPERSONIC SPEEDS BY THE USE OF ACCEL- 
EROMETER AND ATTITUDE -ANGLE MEASURE- 
MENTS. John A. Zalovcik, Lindsay J. Lina and 
James P. Trant, Jr. 1953. ii, 13p. diagrs., 
photos., lab. (NACA Rept. 1145. Formerly 
TN 2099: TN 2570) 

THE ZERO-LIFT DRAG OF A SLENDER BODY OF 
REVOLUTION (NACA RM-10 RESEARCH MODEL) 
AS DETERMINED FROM TESTS IN SEVERAL WIND 
TUNNELS AND IN FLIGHT AT SUPERSONIC 
SPEEDS. Albert J. Evans. 1954. ii, 13p, 
diagrs. , tab. (NACA Rept. 1160. Formerly 
TN 2944) 

SOME POSSIBILITIES OF USING GAS MIXTURES 
OTHER THAN AIR IN AERODYNAMIC RESEARCH. 
Dean R. Chapman. August 1954. 48p. diagrs., 4 
tabs. (NACA TN 3226) 



A TECHNIQUE UTILIZING ROCKET-PROPELLED 
TEST VEHICLES FOR THE MEASUREMENT OF 
THE DAMPING IN ROLL OF STING-MOUNTED 
MODELS AND SOME INITIAL RESULTS FOR DELTA 
AND UNSWEPT TAPERED WINGS. William M. 
Bland, Jr. and Carl A. Sandahl. May 1955. 25p. 
diagrs., photos., tab. (NACA TN 3314. Formerly 
RM L50D24) 

AN NACA VANE-TYPE ANGLE-OF-ATTACK IN- 
DICATOR FOR USE AT SUBSONIC AND SUPERSONIC 
SPEEDS. Jesse L. Mitchell and Robert F. Peck. 
May 1955. 8p. diagrs., photo. (NACA TN 3441. 
Formerly RM L9F28a) 

PROPULSION RESEARCH 
EQUIPMENT 



(9.1.4) 



SOME POSSIBILITIES OF USING GAS MIXTURES 
OTHER THAN AIR IN AERODYNAMIC RESEARCH. 
Dean R. Chapman. August 1954. 48p. diagrs., 4 
tabs. (NACA TN 3226) 

SOME EFFECTS OF EXPOSURE TO EXHAUST -GAS 
STREAMS ON EMITTANCE AND THERMOELECTRIC 
POWER OF BARE-WIRE PLATINUM RHODIUM - 
PLATINUM THERMOCOUPLES. George E. Glawe 
and Charles E. Shepard. August 1954. 30p. diagrs., 
photos. (NACA TN 3253) 



PROPELLER 
(9.1.5) 

INVESTIGATION OF THE NACA 4-(5)(08)-03 TWO- 
BLADE PROPELLER AT FORWARD MACH NUM- 
BERS TO 0.925. James B. Delano and Melvin M. 
CarmeL September 15, 1949. 61p. diagrs., photo. 
(NACA RM L9G06a) 

EFFECT OF COMPRESSIBILITY AND CAMBER AS 
DETERMINED FROM AN INVESTIGATION OF THE 
NACA 4-(3)(08)-03 AND 4-(5)(08)-03 TWO-BLADE 
PROPELLERS UP TO FORWARD MACH NUMBERS 
OF 0.925. Melvin M. Carmel, Francis G. Morgan, 
Jr. and Domenic A. Coppolino. June 29, 1950. 92p. 
diagrs., photo. (NACA RM L50D28) 

INVESTIGATION OF AN NACA 4-(5)(05)-041 FOUR- 
BLADE PROPELLER WITH SEVERAL SPINNERS AT 
MACH NUMBERS UP TO 0.90. Robert M. Reynolds, 
Donald A. Buell and John H. Walker. December 
1952. 86p. diagrs., photos., 6 tabs. (NACA 
RM A52I19a) 

MATERIALS 
(9.1.6) 

HIGH-RESOLUTION AUTORADIOGRAPHY. George 
C. Towe, Henry J. Gomberg and J. W. Freeman, 
University of Michigan. July 1954. ii, 138p. 
diagrs., photos., 9 tabs. (NACA TN 3209) 

A FIBROUS-GLASS COMPACT AS A PERMEABLE 
MATERIAL FOR BOUNDARY -LAYER-CONTROL 
APPLICATIONS USING AREA SUCTION. Robert E. 
Dannenberg, James A. Weiberg and Bruno J. 
Gambucci. January 1955. 20p. diagrs., photos., 
2 tabs. (NACA TN 3388) 



182 RESEARCH EQUIPMENT AND TECHNIQUES 



Technique 
(9.2) 



HIGH-SPEED WIND-TUNNEL TESTS OF A 1/16- 
SCALE MODEL OF THE D-558 RESEARCH AIR- 
PLANE - DYNAMIC PRESSURE AND COMPARISON 
OF POINT AND EFFECTIVE DOWNWASH AT THE 
TAIL OF THE D-558-1. Harold L. Robinson. 
November 4, 1948. 27p. diagrs. (NACA RM L8H05) 

THEORETICAL ANALYSIS OF THE ROLUNG 
MOTIONS OF AIRCRAFT USING A FLICKER-TYPE 
AUTOMATIC ROLL STABILIZATION SYSTEM 
HAVING A DISPLACEMENT-PLUS-RATE 
RESPONSE. Howard J. Curfman, Jr. January 12, 
1949. 29p. diagrs., 2 tabs. (NACA RM L8K23a) 

FLIGHT INVESTIGATION OF THE JETTISONABLE- 
NOSE METHOD OF PILOT ESCAPE USING ROCKET- 
PROPELLED MODELS. Reginald R. Lundstrom and 
Burke R. O'Kelly. June 2, 1949. 27p. diagrs., 
photos., 2 tabs. (NACA RM L9D11) 

INVESTIGATION OF LIFT, DRAG, AND PITCHING 
MOMENT OF A 60° DELTA-WING— BODY COM- 
BINATION (AGARD CALIBRATION MODEL B) IN 
THE LANGLEY 9-INCH SUPERSONIC TUNNEL. 
August F. Bromm, Jr. September 1954. 18p. 
diagrs., photos. (NACA TN 3300) 

LIQUEFACTION OF AIR IN THE LANGLEY 11 -INCH 
HYPERSONIC TUNNEL. Charles H. McLellan and 
Thomas W. Williams. October 1954. 36p. diagrs., 
4 tabs. (NACA TN 3302) 

AN EVALUATION OF NON-NEWTONIAN FLOW IN 
PIPE LINES. Ruth N. Weltmann. February 1955. 
40p. diagrs., tab. (NACA TN 3397) 

A THEORY FOR PREDICTING THE FLOW OF REAL 
GASES IN SHOCK TUBES WITH EXPERIMENTAL 
VERIFICATION. Robert L. Trimpi and Nathaniel B. 
Cohen. March 1955. 69p. diagrs., photo. 
(NACA TN 3375) 

FLIGHT TESTING BY RADIO REMOTE CONTROL - 
FLIGHT EVALUATION OF A BEEP-CONTROL 
SYSTEM. Howard L. Turner, John S. White and 
Rudolph D. Van Dyke, Jr. March 1955. 55p. 
diagrs., photos., tab. (NACA TN 3496. Formerly 
RM A52A29) 

CORRECTIONS 
(9.2.1) 

INVESTIGATION OF THE NACA 4-(5)(08)-03 TWO- 
BLADE PROPELLER AT FORWARD MACH NUM- 
BERS TO 0.925. James B. Delano and Melvin M. 
Carmel. September 15, 1949. 61p. diagrs., photo. 
(NACA RM L9G06a) 

FLIGHT CALIBRATION OF FOUR AIRSPEED 
SYSTEMS ON A SWEPT -WING AIRPLANE AT 
MACH NUMBERS UP TO 1.04 BY THE NACA 
RADAR-PHOTOTHEODOLITE METHOD. Jim 
Rogers Thompson, Richard S. Bray and George E. 
Cooper. October 27, 1950. 41p. diagrs., photos., 
tab. (NACA RM A50H24) 

ERROR IN AIRSPEED MEASUREMENT DUE TO 
STATIC -PRESSURE FIELD AHEAD OF THE WING 
TIP OF A SWEPT-WING AIRPLANE MODEL AT 
TRANSONIC SPEEDS. Edward C. B. Danforth and 
Thomas C. O'Bryan. March 1, 1951. 16p. diagrs., 
photo. (NACA RM L50L28) 



A METHOD OF CALIBRATING AIRSPEED INSTAL- 
LATIONS ON AIRPLANES AT TRANSONIC AND 
SUPERSONIC SPEEDS BY THE USE OF ACCEL- 
EROMETER AND ATTITUDE -ANGLE MEASURE- 
MENTS. John A. Zalovcik, Lindsay J. Lina and 
James P. Trant, Jr. 1953. ii, 13p. diagrs., 
photos., tab. (NACARept. 1145. Formerly 
TN 2099; TN 2570) 

CONSIDERATIONS ON THE EFFECT OF WIND- 
TUNNEL WALLS ON OSCILLATING AIR FORCES 
FOR TWO-DIMENSIONAL SUBSONIC COMPRES- 
SIBLE FLOW. Harry L. Runyan; and Charles E. 
Watkins. 1953. li, 7p. diagrs. (NACA Rept. 1150. 
Formerly TN 2552) 

SOME EFFECTS OF EXPOSURE TO EXHAUST -GAS 
STREAMS ON EMITTANCE AND THERMOELECTRIC 
POWER OF BARE-WIRE PLATINUM RHODIUM - 
PLATINUM THERMOCOUPLES. George E. Glawe 
and Charles E. Shepard. August 1954. 30p. diagrs., 
photos. (NACA TN 3253) 

VISCOSITY CORRECTIONS TO CONE PROBES IN 
RAREFIED SUPERSONIC FLOW AT A NOMINAL 
MACH NUMBER OF 4. L. Talbot, University of 
California. November 1954. 39p. diagrs., photo., 
4 tabs. (NACA TN 3219) 

GENERALIZATION OF GAS-FLOW - 
INTERFEROMETRY THEORY AND 
INTERFEROGRAM EVALUATION EQUATIONS FOR 
ONE-DIMENSIONAL DENSITY FIELDS. Walton L. 
Howes and Donald R. Buchele. February 1955. 70p. 
diagrs, photos. (NACA TN 3340) 

AN NACA VANE -TYPE ANGLE -OF-ATTACK IN- 
DICATOR FOR USE AT SUBSONIC AND SUPERSONIC 
SPEEDS. Jesse L. Mitchell and Robert F. Peck. 
May 1955. 8p. diagrs., photo. (NACA TN 3441. 
Formerly BM. L9F28a) 



AERODYNAMICS 



(9.2.2) 



INVESTIGATION OF THE NACA 4-(5)(08)-03 TWO- 
BLADE PROPELLER AT FORWARD MACH NUM- 
BERS TO 0.925. James B. Delano and Melvin M. 
Carmel. September 15, 1949, 61p. diagrs., photo. 
(NACA RM L9G06a) 

AN 8-FOOT AXISYMMETRICAL FIXED NOZZLE 
FOR SUBSONIC MACH NUMBERS UP TO 0.99 AND 
FOR A SUPERSONIC MACH NUMBER OF 1.2. 
Virgil S. Ritchie, Ray H. Wright and Marshall P. 
Tulin. February 23, 1950. 52p. diagrs., photos., 
2 tabs. (NACA RM L50A03a) 

SUPERSONIC TUNNEL INVESTIGATION BY MEANS 
OF INCLINED-PLATE TECHNIQUE TO DETERMINE 
PERFORMANCE OF SEVERAL NOSE INLETS OVER 
MACH NUMBER RANGE OF 1.72 TO 2.18. Jerome 
L. Fox. February 14, 1951. 27p. diagrs., photos. 
(NACA RM E50K14) 

SKIN-TEMPERATURE TELEMETER FOR 
DETERMINING BOUNDARY-LAYER HEAT- 
TRANSFER COEFFICIENTS. Clifford L. Fricke 
and Francis B. Smith. March 15, 1951. 22p. 
diagrs. (NACA RM L50J17) 



RESEARCH EQUIPMENT AND TECHNIQUES 

TECHNIQUES (9. 2) 



183 



Aerodynamics (Con;t. ) 

PRELIMINARY INVESTIGATION OF THE DRAG 
CHARACTERISTICS OF THE NACA RM-IO MISSILE 
AT MACH NUMBERS OF 1.40 AND 1.59 IN THE 
LANGLEY 4- BY 4-FOOT SUPERSONIC TUNNEL. 
Lowell E, Hasel, Archibald R. Sinclair and Clyde V. 
Hamilton, April 1952. 49p. diagrs., photos, 3 tabs. 
(NACA RM L52A14) 

A PRELIMINARY INVESTIGATION OF SHOCK-WAVE 
REFLECTIONS IN A SMALL CLOSED BALLISTIC 
RANGE WITH VARIOUS TYPES OF WALLS. A. P. 
Sabol. September 1952. 21p. photos., diagrs. 
(NACA RM L52G25) 

DIRECT MEASUREMENTS OF SKIN FRICTION. 
Satish Dhawan, California Institute of Technology. 
1953. ii, 20p. diagrs., photos. (NACA Rept. 1121. 
Formerly TN 2567) 

A VISUALIZATION STUDY OF SECONDARY FLOWS 
IN CASCADES. Howard Z. Herzig, Arthur G. 
Hansen and George R. Costello. 1954. ii, 51p. 
diagrs., photos. (NACA Rept. 1163. Formerly 
TN 2947; RM E52F19) 

INVESTIGATION OF MACH NUMBER CHANGES 
OBTAINED BY DISCHARGING HIGH-PRESSURE 
PULSE THROUGH WIND TUNNEL OPERATING 
SUPERSONICALLY. Rudolph C. Haefeli and Harry 
Bernstein. August 1954. 14p. diagrs., photos., 
tab. (NACA TN 3258) 

RECOVERY CORRECTIONS FOR BUTT -WELDED, 
STRAIGHT -WIRE THERMOCOUPLES IN HIGH- 
VELOCITY, HIGH-TEMPERATURE GAS STREAMS. 
Frederick S. Simmons. September 1954. 19p. 
diagrs. (NACA RM E54G22a) 

A PRELMINARy FLIGHT INVESTIGATION OF AN 
OIL-FLOW TECHNIQUE FOR AIR-FLOW VISUALI- 
ZATION. Harold 1. Johnson and Robert G. Mungall. 
October 1954. 33p. diagrs., photos. (NACA 
RM L54G14a) 

SMOKE STUDY OF NOZZLE SECONDARY FLOWS 
IN A LOW-SPEED TURBINE. Milton G. Kofskey 
and Hubert W. Allen. November 1954. 24p. diagrs. , 
photos. (NACA TN 3260) 



A SYSTEM FOR MEASURING THE DYNAMIC LAT- 
ERAL STABILITY DERIVATIVES IN HIGH-SPEED 
WIND TUNNELS. Henry C. Lessing, Thomas B. 
Fryer and MerriU H. Mead. December 1954. 42p. 
diagrs., photo. (NACA TN 3348) 

A WIND-TUNNEL TEST TECHNIQUE FOR 
MEASURING THE DYNAMIC ROTARY STABILITY 
DERIVATIVES INCLUDING THE CROSS DERIVA- 
TIVES AT HIGH MACH NUMBERS. Benjamin H. 
Beam. January 1955. 35p. diagrs., photos. 
(NACA TN 3347) 

THE LINEARIZED EQUATIONS OF MOTION 
UNDERLYING THE DYNAMIC STABILITY OF AIR- 
CRAFT, SPINNING PROJECTILES, AND SYM- 
METRICAL MISSILES. A. C. Charters. January 
1955. 102p. diagrs. (NACA TN 3350) 

SOME MEASUREMENTS OF TIME AND SPACE 
CORRELATION IN WIND TUNNEL. (Quelques 
Mesures de Correlation Dans le Temps et L'Espace 
en Soufflerie). A. Favre, J. GavigUo and R. Dumas. 
February 1955. 21p. diagrs. (NACA TM 1370. 
Trans, from La Recherche Aeronautlque, no. 32, 
Mar. -Apr., 1953, p. 21-28). 



GENERALIZATION OF GAS- FLOW - 
INTERFEROMETRY THEORY AND 
INTERFEROGRAM EVALUATION EQUATIONS FOR 
ONE-DIMENSIONAL DENSITY FIELDS. Walton L. 
Howes and Donald R. Buchele. February 1955. 70p. 
diagrs, photos. (NACA TN 3340) 

APPARATUS FOR MEASUREMENTS OF TIME AND 
SPACE CORRELATION. (Appareil de Mesures de la 
Correlation Dans le Temps et L'Espace). A. Favre, 
J. GavigUo and R. Dumas. (Presented at eighth In- 
ternational Congress for Theoretical and Applied 
Mechanics, Istanbul, Aug., 1952) April 1955. 20p. 
diagrs., photos. (NACA TM 1371. Trans, from La 
Recherche Aeronautlque, no. 31, Jan.-Feb., 1953, 
p. 37-44). 

A SELF-EXCITED, ALTERNATING-CURRENT, 
CONSTANT -TEMPERATURE HOT-WIRE ANEMOM- 
ETER. Charles E. Shepard. April 1955. 29p. 
diagrs., photos. (NACA TN 3406) 

METHOD OF CONTROLLING STIFFNESS PROPER- 
TIES OF A SOLID-CONSTRUCTION MODEL WING. 
Norman S. Land and Frank T, Abbott, Jr. April 
1955. 21p. diagrs., photos., tab. (NACA TN 3423) 

HEAT-LOSS CHARACTERISTICS OF HOT-WIRE 
ANEMOMETERS AT VARIOUS DENSITIES IN 
TRANSONIC AND SUPERSONIC FLOW. W. G. 
Spangenberg, National Bureau of Standards. May 
1955. 82p. diagrs., photos., 14 tabs. (NACA 
TN 3381) 

HYDRODYNAMICS 
(9.2.3) 

AVERAGE SKIN-FRICTION DRAG COEFFICIENTS 
FROM TANK TESTS OF A PARABOLIC BODY OF 
REVOLUTION (NACA RM-10). Elmo J. Mottard and 
J. Dan Loposer. 1954. ii, 7p. diagrs., photos. 
(NACA Rept. 1161. Formerly TN 2854) 

LOADS AND CONSTRUCTION 
(9.2.4) 

AN INVESTIGATION OF THE USE OF ROCKET- 
POWERED MODELS FOR GUST -LOAD STUDIES 
WITH AN APPLICATION TO A TAILLESS SWEPT- 
WING MODEL AT TRANSONIC SPEEDS. A. James 
Vitale, H. Press and C. C. Shufflebarger. June 
1954. 36p. diagrs., photos., tab. (NACA TN 3161) 

AN EVALUATION OF AN ACCELEROMETER 
METHOD FOR OBTAINING LANDING-GEAR DRAG 
LOADS. Jerome G. Theisen and Philip M. Edge, Jr. 
October 1954. 22p. diagrs., photos. (NACA 
TN 3247) 

METHOD OF CONTROLLING STIFFNESS PROPER- 
TIES OF A SOLID-CONSTRUCTION MODEL WING. 
Norman S. I^and and Frank T. Abbott, Jr. April 
1955. 21p. diagrs., photos., tab. (NACA TN 3423) 



PROPULSION 
(9.2.5) 



THE EFFECTIVENESS OF WING VORTEX GENER- 
ATORS IN IMPROVING THE MANEUVERING CHAR- 
ACTERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, George 
A. Rathert, It. and Richard S. Bray. February 1952. 
45p. photos., diagrs., tab. (NACA RM A51J18) 

A SELF-EXCITED, ALTERNATING-CURRENT, 
CONSTANT -TEMPERATURE HOT-WIRE ANEMOM- 
ETER. Charles E. Shepard. April 1955. 29p. 
diagrs. photos. (NACA TN 3406) 



184 



RESEARCH EQUIPMENT AND TECHNIQUES 
EQUIPMENT (9. 1) 



OPERATING PROBLEMS 
(9.2.6) 

APPLICATIONS OF AUXILIARY AIR INJECTORS TO 
SUPERSONIC WIND TUNNELS. Joseph M. Spiegel, 
Robert U. Hofstetter and Donald M. Kuehn. 
November 1953. 53p. diagrs., photos. (NACA 
RM A53I01) 

A PROCEDURE FOR THE DESIGN OF AIR-HEATED 
ICE -PREVENTION SYSTEMS. Carr B. Neel, Jr. 
June 1954. 63p. diagrs., photo. (NACA TN 3130) 

AN ANALYSE OF SHOCK-WAVE CANCELLATION 
AND REFLECTION FOR POROUS WALLS WHICH 
OBEY AN EXPONENTIAL MASS-FLOW PRESSURE- 
DIFFERENCE RELATION. Joseph M. Spiegel and 
Phillips J. Timnell. August 1954. 23p. diagrs. 
(NACA TN 3223) 

STARTING AND OPERATING LIMITS OF TWO 
SUPERSONIC WIND TUNNELS UTILIZING AUXIL- 
IARY AIR INJECTION DOWNSTREAM OF THE 
TEST SECTION. Henry R. Hunczak and Morris D. 
Rousso. September 1954. 28p. diagrs., photo. 
(NACA TN 3262) 

MATHEMATICS 
(9.2.7) 

THEORETICAL Dn'ESTIGATION OF AN AUTO- 
MATIC CONTROL SYSTEM WITH PRIMARY SENSI- 
TIVITY TO NORMAL ACCELERATIONS AS USED 
TO CONTROL A SUPERSONIC CANARD MISSILE 
CONFIGURATION. Ernest C. Seaberg and Earl F. 
Smith. July 1951. 48p. diagrs., photo., 3 tabs. 
(NACA RM L51D23) 

SYSTEM ANALYSES AND AUTOPILOT DESIGN FOR 
AUTOMATIC ROLL STABIUZATION OF A SUPER- 
SONIC PILOTLESS AIRCRAFT. Jacob Zarovsky. 
July 1951. 55p. diagrs., tab. (NACA RM L51E07) 

LONGITUDINAL FREQUENCY -RESPONSE CHARAC- 
TERISTICS OF A 35° SWEPT -WING AIRPLANE AS 
DETERMINED FROM FUGHT MEASUREMENTS, 
INCLUDING A METHOD FOR THE EVALUATION OF 
TRANSFER FUNCTIONS. WiUiam C. Triplett and G. 
Allan Smith. September 1951. 45p. diagrs., photo. 
(NACA RM A51G27) 



A THEORETICAL INVESTIGATION OF THE INFLU- 
ENCE OF AUTOPILOT NATURAL FREQUENCY 
UPON THE DYNAMIC PERFORMANCE CHARAC- 
TERISTICS OF A SUPERSONIC CANARD MISSILE 
CONFIGURATION WITH A PITCH -ATTITUDE CON- 
TROL SYSTEM. Anthony L. Passera. October 
1951. 32p. diagrs., photos., 2 tabs. (NACA 
RM L51H02) 

A STUDY OF THE APPLICATION OF POWER- 
SPECTRAL METHODS OF GENERALIZED HARMON- 
IC ANALYSE TO GUST LOADS ON AIRPLANES. 
Harry Press and Bernard Mazelsky. 1954. li, 17p. 
diagrs., 2 tabs. (NACA Hept. 1172. Formerly 
TN 2853) 

AN ANALYTICAL INVESTIGATION OF AIRPLANE 
SPIN-RECOVERY MOTION BY USE OF ROTARY- 
BALANCE AERODYNA»«C DATA. Stanley H. Scher. 
June 1954. 38p. diagrs., tab. (NACA TN 3188) 

THE SMALL-DISTURBANCE METHOD FOR FLOW 
OF A COMPRESSIBLE FLUID WITH VELOCITY 
POTENTIAL AND STREAM FUNCTION AS INDE- 
PENDENT VARIABLES. Carl Kaplan. August 1954. 
18p. (NACA TN 3229) 

SOME MEASUREMENTS AND POWER SPECTRA OF 
RUNWAY ROUGHNESS. James H. Walls, John C. 
Houbolt and Harry Press. November 1954. 27p. 
diagrs., tab. (NACA TN 3305) 

ON THE ANALYSIS OF LINEAR AND NONLINEAR 
DYNAMICAL SYSTEMS FROM TRANSIENT- 
RESPONSE DATA. Marvin Shinbrot. December 
1954. 51p. diagrs., 6 tabs. (NACA TN 3288) 

ANALYTICAL DETERMINATION OF THE 
MECHANISM OF AN AIRPLANE SPIN RECOVERY 
WITH DIFFERENT APPLIED YAWING MOMENTS 
BY USE OF ROTARY-BALANCE DATA. Sanger M. 
Burk, Jr. December 1954. 43p. diagrs., 2 tabs. 
(NACA TN 3321) 

ON THE SMALL-DISTURBANCE ITERATION 
METHOD FOR THE FLOW OF A COMPRESSIBLE 
FLUID WITH APPUCATION TO A PARABOLIC 
CYLINDER. Carl Kaplan. January 1955. 36p. 
diagrs., tab. (NACA TN 3318) 

THEORETICAL INVESTIGATION OF A 
PROPORTIONAL-PLUS-FLICKER AUTOMATIC 
PILOT. Ernest C. Seaberg. May 1955. 53p. 
diagrs., photo., tab. (NACA TN 3427. Formerly 
RM L50I19) 



ALPHABETICAL SUBJECT INDEX 




185 



Subject Heading Outline 



Subject 

Heading 

Nttmber 



Subject Heading Outline 



Subject 

Heading 

Number 



Accessories and Accessory Functions 
See also 

Cooling Systems 

Fuel Systems 

Ignition Systems 
Accessories Ice Prevention and Removal 
Adhesives 
Aerodynamic Loads 
See also 

Aerodynamic Loads - Fuselage, 
Nacelles, and Canopies 

Aerodynamic Loads, Rotating Wings 

Aerodynamic Loads, Tail 

Aerodynamic Loads, Wings 

Aeroelasticity 
Aerodynamic Loads - Fuselage, Nacelles, 
and Canopies (4 

Aerodynamic Loads, Rotating Wings (4 
Aerodynamic Loads, Tail (4 

See also 

Buffeting and Gust Loads, Tail 

Maneuvering Loads, Tail 

Steady Loads, Tail 
Aerodynamic Loads, Wings (4 

See also 

Gust Loads, Wings 

Maneuvering Loads, Wings 

Steady Loads, Wings 
Aerodynamics 
See also 

Aerodynamics, Fundamental 

Aeroelasticity 

Aircraft 

Bodies 

Internal Aerodynamics 

Parachutes 

Propellers 

Rotating Wings 

Stability and Control, Aerodynamic 

Wings 
Aerodynamics, Fundamental 
See also 

Aerodynamics With Heat 

Compressible Flow 

Flow of Rarefied Gases 

Incompressible Flow 

Viscous Flow 
Aerodynamics With Heat 
See also 

Heat, Addition of - Aerodynamic 

Heat Transfer, Aerodynamic 

Heating, Aerodynamic 
Aerodynamics, Internal 
See 

Internal Aerodynamics 
Aerodynamics Research Technique 



(3. 12) 



(7. 3. 5) 
(5.1.8) 
(4.1.1) 



1.1.3) 
1.1.4) 
1. 1. 2) 



1. 1. 1) 



(1) 



(1.1) 



(1.1.4) 



(4 

(3.3 

(4 



(1.8 



Aeroelasticity (1. 

Aeroelasticity, Loads (4. 1. 1. 

Afterburning, Gas Turbines 
Ailerons, Vibration and Flutter 
Air Inlets 
See 

Inlets 
Air Brakes 
Aircraft 
See also 

Airplanes 

Missiles 

Rdtating-Wing Aircraft 

Seaplanes 
Aircraft Construction 
See 

Aircraft Loads and Construction 
Aircraft Loads and Construction 
See also 

Loads 

Structures 

Vibration and Flutter 
Airplane Performance 
Airplanes 
See also 

Airplanes, Specific Types 

Components in Combination 

Performance, Airplanes 
Airplanes, Specific Types 
All-Movable Controls, Complete Wings (1 
Aluminum 
Amphibians 
See 

Hydrodynamics 
Antifriction Bearings (3. 8 

Aspect Ratio, Complete Wings (1.2.2 

Atmosphere 
See also 

Gusts 
Atomization, Fuel 
See 

Combustion, Effects of Fuel Atomization 

Fuels, Physical and Chemical Properties 



9) 
5) 
2) 
1) 



4) 
7) 



(4) 



(1.7. 
(1. 



(1.7.1. 

.2.2.4. 

(5.1. 



3) 
1) 



2) 
3) 
1) 



1) 
2) 
1) 



Autogiros 

Automatic Control, Aerodynamic 
Automatic Stabilization 
Auxiliary Booster Systems 
See also 
Gas Turbines, Auxiliary Booster 
Systems 

Axial-Flow Compressors 
Axial-Flow Txirbines 



(1.7. 
(1.8. 



3. 
2. 

(1.8. 
(3. 



(3.6. 
(3.7. 



1) 
6) 
8) 
3) 



1) 
1) 



B 



(9. 2. 2) 



Beams, Structural 
See also 
Box Beams 



(4.3.4) 



186 



Subject Heading Outline 



Subject 

Heading 

Number 



Subject Heading Outline 



Subject 

Heading 

Number 



Bearings 
See 
Antifriction Bearings 
Bending, Structural (4.3.7.3) 

Bends, Internal Aerodynamics (1. 4. 2. 4) 

Blade Plan Forms, Propellers (1.5.2.4) 

Blade Sections, Propellers (1. 5. 2. 1) 

Bodies (1. 3) 

See also 
Bodies, Theory 
Canopies 
Ducted Bodies 
Hulls 

Shape Variables, Bodies 
Bodies, Theory (1. 3. 1) 

Body-Wing Combinations, Missiles (1. 7. 2. 1. 1) 
Bolted Connections (4. 3. 6. 1) 

Booster Systems, Auxiliary 
See 
Auxiliary Booster Systems 
Booster Systems, Auxiliary - Gas 
Turbines 
See 
Gas Turbines, Auxiliary Booster 
Systems 
Boundary Layer Characteristics, 

Complete Wings (1.2.2.8.1) 

Boundary Layer Characteristics - 

Internal Aerodynamics (1. 4. 7. 1) 

Boundary Layer Characteristics, Wing 

Sections (1.2.1.6.1) 

Boundary Layer, Complete Wings (1. 2. 2. 8) 

See also 
Boundary Layer Characteristics, 

Complete Wings- 
Boundary Layer Control, Complete 
Wings 
Boundary Layer Control, Complete 

Wings (1.2.2.8.2) 

Boundary Layer Control, Internal 

Aerodynamics (1.4.7.2) 

Boundary Layer Control, Wing 

Sections (1.2.1.6.2) 

Boundary Layer, Internal Aerodynamics (1. 4. 7) 
See also 
Boundary Layer Characteristics, 

Internal Aerodynamics 
Boundary Layer Control, Internal 
Aerodynamics 
Boundary Layer, Wing Sections (1. 2. 1. 6) 

See also 
Boimdary Layer Characteristics, 

Wing Sections 
Boundary Layer Control, Wing 
Sections 
Box Beams (4. 3. 4. 1) 

Boxes, Structural (4. 3. 5. 2) 

Buffeting and Gust Loads, Tail (4. 1. 1. 2. 3) 



Camber, Wing Section (1. 2. 1. 2. 1) 

Canopies (1. 3. 3) 

Canopy Loading 
See 
Loads, Fuselage, Nacelle, and 
Canopy 
Cascades, Experiment (1.4.5.2) 

Cascades, Internal Aerodynamics (1.4.5) 

See also 
Cascades, Experiment 
Cascades, Theory 
Cascades, Theory (1.4.5.1) 

Centrifugal Compressors 
See 
Radial Flow Compressors 
Ceramals (5.1.12) 

Ceramics (5, 1. 5) 

Chemistry of Lubrication (3. 8. 1. 2) 

Chines, Seaplane Hulls (2. 3. 6) 

Columns, Structural (4. 3. 1) 

Combustion and Combustors (3. 5) 

See also 
Combustion Research, General 
Combustion, Effect of Engine Operating 
Conditions and Combustion-Chamber 
Geometry (3.5.2) 

See also 
Ramjet Engines, Combustion 
Rocket Engines, Combustion 
Turbine Engines, Combustion 
Combustion, Effects of Fuel Atomization (3. 5. 1. 4) 
Combustion - Relation to Specific Engine 
T3^es 
See 
Combustion, Effect of Engine 
Operating Conditions and 
Combustion-Chamber Geometry 
Combustion Research, General (3. 5. 1) 

See also 
Fuel Atomization, Effects on 

Combustion 
Ignition of Gases 
Laminar-Flow Combustion 
Reaction Mechanisms 
Turbulent-Flow Combustion 
Components in Combination, Airplanes (1. 7. 1. 1) 
See also 
External Stores, Effects - Airplanes 
Tail-Wing-Fuselage Combinations - 

Airplanes 
Wing-Fuselage Combinations, Airplanes 
Wing-Nacelle Combinations, Airplanes 
Components in Combination, Missiles (1. 7. 2. 1) 
See also 
Interference, Jet, - Missiles 



187 



Subject Heading Outline 



Subject 

Heading 

Number 



Subject Heading Outline 



Subject 

Heading 

Number 



Tail-Body Combinations, Missiles 
Wing-Body Combinations, Missiles 
Wing-Tail-Body Combinations, 
Missiles 
Compressible Flow (1. 1. 2) 

See also 
Mixed Flow 
Subsonic Flow 
Supersonic Flow 
Compression and Compressors (3. 6) 

See also 
Compressor Flow Theory and 

Experiment 
Matching, Compressors 
Stress and Vibration, Compressors 
Compression in Structures 
Compressive Properties of Materials 
Compressor Flow Theory and 
Experiment 
See also 
Axial-Flow Compressors 
Mixed-Flow Compressors 
Radial-Flow Compressors 
Compressor Stresses 
Compressor Vibration 
Compressors and Compression 
Concentrated Loads and Stresses 
Configurations, Hydrodynamic 
Connections, Structural 
See also 
Bolted Connections 
Riveted Connections 
Control, Aerodynamic 
See also 
Air Brakes 

Automatic Control, Aerodynamic 
Directional Control 
Hinge Moments 
Lateral Control 
Longitudinal Control 
Control and Stability, Aerodynamic 
See 
Stability and Control, Aerodynamic 
Control and Stability, Hydrodynamic 
See 
Stability and Control, Hydrodynamic 
Control of Engines (3. 2) 

See also 
Turbine -Propeller Engines, Control 
Turbine-Ram-Jet Engines, Control 
Turbojet Engines, Control 
Controls, Complete Wings (1. 2. 2. 4) 

See also 
All-Movable Controls, Complete 

Wings 
Flap-Type Controls, Complete 

Wings 
Spoilers, Controls - Complete 
Wings 



(4. 3. 7. 2) 
(5.2.2) 

(3. 6. 1) 



(3.6.2) 
(3. 6. 2) 

(3.6) 
(4.3.7.6) 

(2.2) 
(4. 3. 6) 



(1.8.2) 



Controls, Flap-Type - Complete Wings 
Controls, Flap-Type - Wing Sections 
Controls, Spoilers - Complete Wings 
Controls, Wing Sections 
See also 
Flap-Type Controls, Wing Sections 
Spoilers, Controls - Wing Sections 
Cooling of Engines 
See also 
Gas-Turbine Systems, Cooling 
Ram -Jet Cooling 
Cooling, Gas Turbines 
Cooling Systems 

Corrections, Research Technique 
Corrosion Resistance Properties of 

Materials 
Crash 
See 
Safety, Operations 
Creep Properties of Materials 
Cross Section, Bodies 
Curved Plates, Structural 
See also 
Curved Plates, Unstiffened 
Curved Plates, Unstiffened 
Cylinders, Circular - Structural 
Cylinders, Structural 
See also 
Cylinders, Circular - Structural 



(1.2,2,4.1) 

(1.2,1.5,1) 

(1.2.2.4.2) 

(1. 2. 1. 5) 



(3. 10) 



(3. 10. 2) 

(3.12.5) 

(9. 2. 1) 

(5.2.8) 



(5.2.3) 
(1.3,2,2) 
(4, 3, 3. 2) 



(4. 3, 3, 2. 1) 

(4. 3, 5. 1. 1) 

(4. 3. 5. 1) 



Damping Derivatives, Stability 

Deadrise, Seaplane Hulls 

Designated Profiles, Wing Sections 

Diffusers, Internal Aerodynamics 
See also 
Subsonic Diffusers 
Supersonic Diffusers 

Dihedral, Complete Wings 

Directional Control 

Directional and Lateral Stability, 
Dynamic 

Directional Stability, Static 

Dual Rotation, Propellers 

Ducted Bodies 
See also 
Nose Shape, Ducted Bodies 
Side Exits, Ducted Bodies 
Side Inlets, Ducted Bodies 

Ducts, Internal Aerodynamics 
See also 
Bends, Internal Aerodynamics 
Diffusers, Internal Aerodynamics 
Nozzles, Internal Aerodynamics 
Pipes, Internal Aerodynamics 



(1.8.1.2.3) 

(2.3.2) 

(1.2.1.3) 

(1.4.2.1) 



(1.2.2,2.7) 
(1.8.2.3) 

(1. 8. 1. 2. 2) 

(1,8,1,1,3) 

(1,5,2,7) 

(1.3.4) 



(1.4.2) 



188 



Subject Heading Outline 



Subject 

Heading 

Number 



Subject Heading Outline 



Subject 

Heading 

Number 



Dynamic Loads and Stresses (4, 3. 7. 7) 

See also 
Repeated Dynamic Loads and 

Stresses 
Transient Dynamic Loads and 
Stresses 
Dynamic Stability (1. 8. 1. 2) 

See also 
Damping Derivatives, Stability 
Lateral and Directional Stability, 

Dynamic 
Longitudinal Stability, Dynamic 



E 



Engine Types, Comparisons (3. 1. 12) 

Engines 

See 
Propulsion Systems, Complete 
Exhaust Energy Recovery, Reciprocating 

Engines 

See 
Reciprocating Engines With Turbines 
Exits and Inlets, Wing Sections (1. 2. 1. 2. 4) 

Exits, Internal Aerodynamics (1.4.3) 

External Stores, Effects - Airplanes (1. 7. 1. 1. 5) 



Fans, Vibration and Flutter (4. 2. 4) 

Fatigue Properties of Materials (5. 2. 5) 

Fineness Ratio, Bodies (1. 3. 2. 1) 

Fire Hazards (7. 9) 

Fire Prevention 

See 
Safety, Operations 
Flap-Type Controls, Complete Wings (1. 2. 2. 4 
Flap-Type Controls, Wing Sections (1. 2. 1. 5 
Flaps, Leading -Edge - Complete Wings (1 
Flaps, Leading -Edge - Wing Sections 
Flaps, Plain - Wing Sections 
Flaps, Split - Wing Sections 
Flaps, Trailing-Edge -Complete Wings 
Flat Plates, Stiffened 
Flat Plates, Structural 

See also 
Flat Plates, Stiffened 
Flat Plates, Unstiffened 
Flat Plates, Unstiffened (4. 

Flexural Properties of Materials 
Flight Instruments 



(1 
(1 
(1 
(1 
(4. 3. 3, 



1) 
1) 

2. 3. 3) 

1.4. 

1.4. 

1.4. 



.4) 
1) 
2) 



3.1) 
1.2) 
(4. 3. 3. 1) 



3.3.1.1) 

(5.2.7) 

(8.1) 



Flight Operations 
See 
Operating Problems 
Flow of Rarefied Gases (1. 1. 5) 

Flutter and Vibration 
See 
Vibration and Flutter 
Flying Boats 
See 
Hydrodynamics 
Flying Qualities (1. 8. 5) 

Frames, Gridworks, and Trusses (4. 3. 2) 

Free-Flight Research Equipment (9. 1. 2) 

Friction and Lubrication (3. 8) 

See also 

Friction and Lubrication Theory and 

Experiment 
Lubricants 

Rolling Contact Surfaces 
Sliding Contact Surfaces 
Sliding and Rolling Contact Surfaces 
Friction and Lubrication Theory and 
Experiment (3. 8. 1) 

See also 
Chemistry of Lubrication 
Hydrodynamic Theory of Lubrication 
Surface Conditions, Friction and 
Lubrication 
Fuel Atomization, Effects on Combustion (3. 5 



Fuel Systems (3. 

See also 
Fuel Systems, Rocket Engines 
Fuel Systems, Rocket Engines (3. 12 

Fuels 
See also 
Fuels, Physical and Chemical 

Properties 
Fuels, Relation to Engine 
Performance 
Fuels, Physical and Chemical 

Properties (3 

Fuels, Relation to Engine Performance (3 
See also 
Fuels - Rockets (Includes Fuel 

and Oxidant) 
Fuels - Turbine Engines, Ram Jets, 
and Pulse Jets 
Fuels - Rockets (Includes Fuel and 

Oxidant) (3. 4 

Fuels - Turbine Engines, Ram Jets, 

and Pulse Jets (3. 4 

Fuselage Loading 
See 
Loads, Fuselage, Nacelle, and 
Canopy 
Fuselage-Wing Combinations, 

Airplanes (1. 

Fuselage-Wing-Tail Combinations - 
Airplanes (1. 



.1.4) 
12.1) 



.1.8) 
(3.4) 



.4.2) 
4.3) 



,3.3) 
,3.2) 



7.1. 



7.1. 



1.1) 
1.3) 



189 



Subject Heading Outline 



Gas Turbine Engines 
See 
Propulsion Systems, Complete 
Gas Turbine Engines, Control 
See 

Turbine-Propeller Engines, Control 
Turbojet Engines, Control 
Gas -Turbine Systems, Cooling 
Gas Turbines, Auxiliary Booster 
Systems 
See also 
Afterburning, Gas Turbines 
Liquid Injection, Gas Turbines 
Gases, Ignition of 
Gases, Properties of 
See also 
Kinetic Properties 
Thermodynamic Properties of Gases 
Gases, Rarefied, Flow of 
See 
Flow of Rarefied Gases 
General Studies, Seaplanes 
Gridworks, Frames, and Trusses 
Gust Alleviation 

Gust and Buffeting Loads, Tail (4 

Gust Loads, Wing (4 

Gust Structure 
Gust Turbulence 
Gusts 
See also 
Gust Alleviation 
Gust Structure 
Gust Turbulence 
Gyroscopic and Mass Problems, 
Aerodynamic 
See 
Mass and Gyroscopic Problems, 
Aerodynamic 



H 



Handling Qualities 
See 

Flying Qualities 
Heat, Addition of, Aerodynamic (1.1.4.3) 

Heat Exchangers (3. 9. 2) 

Heat-Resisting Alloys (5. 1. 4) 

Heat Transfer (3. 9) 

See also 

Heat Exchangers 

Heat Transfer Theory and Experiment 
Heat Transfer, Aerodynamic (1.1.4.2) 

Heat Transfer, Theory and Experiment (3. 9. 1) 
Heating, Aerodynamic (1,1.4.1) 



Subject 




Subject 


Heading 




Heading 


Number 


Subject Heading Outline 


Number 




Helicopters 


(1.7.3.2) 




High- Lift Devices, Complete Wings 


(1. 2. 2. 3) 




See also 






Flaps, Leading-Edge - Complete 






Wings 






Flaps, Trailing-Edge - Complete 






Wings 






Slots and Slats, Complete Wings 






High-Lift Devices, Wing Sections 


(1.2.1.4) 




See also 




(3. 10. 2) 


Flaps, Leading-Edge - Wing Section 
Flaps, Plain - Wing Sections 




(3.3.2) 


Flaps, Split - Wing Sections 






Hinge Moments 


(1.8.2.5) 




Hull Variables, Seaplane 






See 




(3.5.1.6) 


Seaplane Hull Variables 




(3. 11) 


Hulls 


(1.3.5) 




Hydrodynamic Configurations 


(2.2) 




Hydrodynamic Research Technique 


(9. 2. 3) 




Hydrodynamic Theory 


(2.1) 




Hydrodynamic Theory of Lubrication 


(3.8.1.1) 




Hydrodynamics 


(2) 




See also 




(1.7.4.1) 


Hydrodynamic Configurations 




(4. 3. 2) 


Hydrodynamic Theory 




(6. 1. 2. 4) 


Hydrofoils 




.1.1.2.3) 


Planing Surfaces, Hydrodynamic 




.1.1.1.3) 


Seaplane Hull Variables 




(6. 1. 2. 1) 


Stability and Control, Hydrodynamic 




(6. 1. 2. 3) 


Surface Craft 




(6.1.2) 


Hydroflap 
See 
Planing Surfaces, Hydrodynamic 






Hydrofoils 


(2.7) 



Ice Formation (6. 2) 

Ice Presention and Removal (7. 3) 

See also 
Accessories Ice Prevention and 

Removal 
Propeller Ice Prevention and Removal 
Propulsion Systems Ice Prevention 

and Removal 
Windshields Ice Prevention and 

Removal 
Wings and Tails Ice Prevention and 
Removal 
Ignition of Gases (3. 5. 1. 6) 

Ignition Systems (3. 12. 2) 

Incompressible Flow (1. 1. 1) 

Inlets (1.4.1) 

See also 
Inlets, Nose - Annular 
Inlets, Nose - Central 



190 



Subject Heading Outline 



Subject 

Heading 

Number 



Subject Heading Outline 



Subject 

Heading 

Number 



Propeller- 
Subsonic 
Supersonic 



Inlets, Side 

Inlets, Wing-Leading-Edge 
Inlets, Central - Propeller-Spinner 

Cowl 
Inlets, Central - Subsonic 
Inlets, Certral - Supersonic 
Inlets and Exits, Wing Sections 
Inlets, Nose - Annular 
Inlets, Nose - Central 
See also 
Inlets, Central 
Spinner -Cowl 
Inlets, Central 
Inlets, Central 
Inlets, Side 
See also 
Scoops 

Submerged Inlets 
Inlets, Wing-Leading-Edge 
Instruments 
See also 
Flight Instruments 
Laboratory Instruments 
Meteorological Instruments 
Interference, Jet - Missiles 
Interference of Bodies, Propellers 
Intermittent Ramjet 
See 
Pulse Jet Engines 
Internal Aerodynamics 
See also 
Boundary Layer, Internal 

Aerodynamics 
Cascades, Internal Aerodynamics 
Ducts, Internal Aerodynamics 
Exits, Internal Aerodynamics 
Inlets 
Pumps, Jet and Thrust Augmentors 



(1.4. 
(L4. 
(1.4. 
(1.2. 

(1. 

(1. 



1. 1. 1) 
1. 1. 2) 
1.1.3) 
1. 2. 4) 
4. 1. 2) 
4. 1. 1) 



(1.4.1.4) 



(1. 



(1.7. 
(1. 



4. 1. 3) 
(8) 



2. 1. 3) 
5. 2. 8) 



(1.4) 



Jet-Driven Rotors 
Jet Engine Fuels 
See 

Pulse Jet Engines, Fuels 

Ramjet Engines, Fuels 

Rocket Fuels 

Turbine Engines, Fuels 
Jet Mixing 

Jet Propulsion Engines 
See 

Propulsion Systems, Complete 



K 



Kinetic Properties of Gases 



(8. 1. 9) 



(1.1.3.3) 



(3. 11. 1) 



Laboratory Instruments 
Laminar Flow 
Laminar -Flow Combustion 
Laminated Materials 
Landing Loads 
See also 
Loads, Landing - Ground-Run 
Loads, Landing - Impact 
Prelanding Conditions 
Lateral Control 
Lateral and Directional Stability, 

Dynamic 
Lateral Stability, Static 
Length-Beam Ratio, Seaplane Hulls 
Liquid Injection, Gas Turbines 
Loads 
See also 
Aerodynamic Loads 
Landing Loads 
Loads and Construction, Research 

Technique 
Loads and Stresses, Structural 
See also 
Bending in Structures 
Compression in Structures 
Concentrated Loads and Stresses 
Dynamic Loads and Stresses 
Normal Pressures 
Shear in Structures 
Torsion in Structures 
Loads, Fuselage, Nacelle and Canopy 
Loads, Landing - Ground-Run 
See also 
Loads, Landing - Ground-Run, 
Land 
Loads, Landing - Ground-Run, 

Land 
Loads, Landing - Impact 
See also 
Loads, Landing - Impact, Land 
Loads, Landing - Impact, Water 
Loads, Landing - Impact, Land 
Loads, Landing - Impact, Water 
Loads, Tail 
See also 
Buffeting and Gust Loads, Tail 
Maneuvering Loads, Tail 
Steady Loads, Tail 
Loads, Wing 
See also 
Gust Loads, Wing 
Maneuvering Loads, Wing 
Steady Loads, Wing 
Longitudinal Control 
Longitudinal Stability and Control, 

Hydrodynamlc 
Longitudinal Stability, Oyimmic 



(8.2) 

(LI. 3.1) 

(3. 5. 1. 1) 

(5. 1. 11) 

(4. 1. 2) 



(1. 8. 2. 2) 

(L 8. 1.2.2) 

(1. 8. 1. 1. 2) 

(2. 3. 1) 

(3. 3, 2. 1) 

(4.1) 



(9.2.4) 
(4. 3. 7) 



(4. 1. 1. 3) 
(4. 1. 2. 2) 



(4. 1. 2. 2. 1) 
(4. 1. 2. 1) 



(4. 1. 2. 1. 1) 

(4. 1. 2. 1. 2) 

(4. 1. 1. 2) 



(4. 1. 1. 1) 



(1. 8. 2. 1) 

(2. 10. 1) 
(1. 8. 1. 2. 1) 



191 



Subject Heading Outline 



Longitudinal Stability, Static 
Lubricants 

Lubrication, Chemistry of 
Lubication and Friction 
See 
Friction and Lubrication 
Lubrication, Hydrodynamic Theory 



M 



Subject 




Heading 




Number 


Subject Heading Outline 


.8.1.1.1) 


N 


(3.8.5) 




(3. 8. 1. 2) 






Nacelle Loads 




See 




Loads, Fuselage, Nacelle and 


(3.8.1.1) 


Canopy 




Nacelle-Wing Combinations, Airplanes (1 




Noise 




Normal Pressures 




Nose Inlets, Internal Aerodynamics 




Nose Shape, Ducted Bodies 


(1.2.2.6) 


Nozzles, Internal Aerodynamics 


(1.5.2.5) 


Nuclear-Energy Systems 



Mach Number Effects, Complete Wings (1. 2. 2. 6) 


Nozzles, Internal Aerodynamics 


(L4.2.2) 


Mach Number Effects, Propellers 


(1.5.2.5) 


Nuclear-Energy Systems 


(3. 1. 10) 


Mach Number Effects, Wing Sections 


(1.2.1.8) 






Maneuvering Loads, Tail 


(4. 1. 1. 2. 2) 






Maneuvering Loads, Wing 


(4. 1. 1. 1. 2) 







Mass and Gyroscopic Problems, 








Aerodynamic 


(1.8.6) 






Matching, Compressors 


(3. 6. 3) 


Operating Conditions, Propellers 


(1.5.6) 


Matching, Turbines 


(3.7.4) 


Operating Problems 


(7) 


Materials 


(5) 


See also 




See also 




Fire Hazards 




Materials, Types 




Ice Prevention and Removal 




Operating Stresses and Conditions 




Noise 




of Materials 




Operating Problems, General 




Properties of Materials 




Physiological Operating Problems 




Materials, Research Equipment 


(9.1.6) 


Piloting Techniques 




Materials, Types 


(5.1) 


Safety, Operations 




See also 




Operating Problems, General 


(7. 10) 


Adhesives 




Operating Problems, Research Techniqi 


lie (9.2.6) 


Aluminum 




Operating Stresses and Conditions of 




Ceramals 




Materials 


(5.3) 


Ceramics 




Oxidants 




Heat-Resisting Alloys 




See 




Laminated Materials 




Rocket Fuels 




Plastics 








Protective Coatings 








Sandwich Materials 




P 




Steels 








Woods 








Mathematics, Research Technique 


(9. 2. 7) 


Parachutes 


(1. 10) 


Meteorological Instruments 


(8.3) 


Performance, Airplanes 


(1. 7. 1. 3) 


Meteorology 


(6) 


Physiological Operating Problems 


(7.8) 


See also 




Pilot-Escape Techniques 


(7. 1. 1) 


Atmosphere 




Piloting Techniques 


(7.7) 


Ice Formation 




Pipes, Internal Aerodynamics 


(1.4.2.3) 


Missiles 


(1.7.2) 


Pitch and Yaw, Propellers 


(1.5.2.9) 


See also 




Planing Surfaces, Hydrodynamic 


(2.6) 


Components in Combination, Missiles 


Planing Tail Hulls 




Missiles, Specific Types 




See 




Missiles, Specific Types 


(1.7.2.2) 


Seaplane Hull Variables 




Mixed Flow 


(LI. 2. 2) 


Plasticity 


(5. 2. 13) 


Mixed Flow Compressors 


(3.6.1.3) 


Plastics 


(5.1.6) 


Models 




Plates, Structural 


(4.3.3) 


See 




See also 




Aircraft 




Curved Plates, Structural 




Multiaxial Stress of Materials 


(5. 2. 12) 


Flat Plates, Structural 





192 



Subject Heading Outline 

Power Plants 
See 
Propulsion Systems, Complete 

Prelanding Conditions 

Profiles, Complete Wings 

Profiles, Designed, Wing Sections 

Propeller Design Variables 
See also 
Blade Plan Forms, Propellers 
Blade Sections, Propellers 
Dual Rotation, Propellers 
Interference of Bodies, Propellers 
Mach Number Effects, Propellers 
Pitch and Yaw, Propellers 
Pusher, Propellers 

Propeller Ice Prevention and Removal 

Propeller Operating Conditions 

Propeller Research Equipment 

Propeller Slipstream 

Propeller-Spinner-Cowl Combinations 

Propeller Theory 

Propeller Vibration and Flutter 

Propellers 
See also 
Propeller Design Variables 
Propeller Operating Conditions 
Propeller Slipstream 
Propeller -Spinner-Cowl Combinations 
Propeller Theory 
Propellers, Designated Types 

Propellers, Designated Types 

Properties of Gases 
See also 
Kinetic Properties of Gases 
Thermodynamic Properties of Gases 

Properties of Materials 
See also 
Compressive Properties of Materials 
Corrosion Resistance, Properties 

of Materials 
Creep Properties of Materials 
Fatigue Properties of Materials 
Flexural Properties of Materials 
Multiaxial Stress of Materials 
Plasticity 

Shear Properties of Materials 
Stress -Rupture Properties of 

Materials 
Structural Properties of Materials 
Tensile Properties of Materials 
Thermal Properties of Materials 

Propulsion 
See also 
Accessories and Accessory Functions 
Auxiliary Booster Systems 
Combustion and Combustors 
Compression and Compressors 
Control of Engines 
Cooling of Engines 



Subject 




Subject 


Heading 




Heading 


Number 


Subject Heading Outline 

Friction and Lubrication 

Fuels 

Heat Transfer 


Number 


(4. 1. 2. 3) 


Properties of Gases 




(1. 2. 2. 2. 1) 


Propulsion Systems, Complete 




(1. 2. 1. 3) 


Turbines 




(1.5.2) 


Vibration and Flutter, Propulsion 






Propulsion Research Equipment 


(9.1.4) 




Propulsion Research Technique 


(9. 2. 5) 




Propulsion Systems, Complete 


(3. 1) 




See also 






Engine Types, Comparisons 






Jet -Driven Rotors 






Nuclear -Energy Systems 






Ram -Jet Engines 




(7, 3. 2) 


Reciprocating Engines 




(1. 5. 6) 


Rocket Engines 




(9. 1. 5) 


Turbo-Propeller Engines 




(1.5.4) 


Turbojet Engines 




(1. 5. 7) 


Propulsion Systems, Ice Prevention 




(1. 5. 1) 


and Removal 


(7.3.6) 


(4.2.4) 


Protective Coatings 


(5.1.9) 


(1.5) 


Protuberances, Bodies 


(1.3.2.5) 




Pulse Jet Engines, Fuels 


(3.4.3.2) 




Pumps, Jet and Thrust Augmentors 


(1.4.4) 




Pusher, Propellers 


(1. 5. 2. 6) 



(1.5.3) 
(3. 11) 



(5.2) 



(3) 



Radial-Flow Compressors 

Radial-Flow Turbines 

Ram -Jet Cooling 

Ram-Jet Engines 

Ram-Jet Engines, Combustion 

Ram-Jet Engines, Fuels 

Rarefied Gases, Flow of 
See 
Flow of Rarefied Gases 

Reaction Mechanisms 

Reciprocating Engines 

Repeated Dynamic Loads and Stresses 

Research Equipment 
See also 
Free-Flight Research Equipment 
Materials Research Equipment 
Propeller Research Equipment 
Propulsion Research Equipment 
Wind Tunnels 

Research Equipment and Techniques 
See also 
Research Equipment 
Research Techniques 

Research Techniques 
See also 
Aerodynamic Research Technique 
Corrections, Research Technique 
Hydrodynamic Research Technique 



(3. 6. 1. 2) 
(3. 7. 1. 2) 
(3. 10. 3) 
(3.1.7) 
(3. 5. 2. 3) 
(3.4.3.2) 



(3. 5. 1. 5) 

(3. 1. 1) 

(4. 3. 7. 7. 1) 

(9.1) 



(9) 



(9.2) 



193 



Subject Heading Outline 



Subject 

Heading 

Number 



Subject Heading Outline 



Subject 

Heading 

Number 



(1.2. 


1.7) 


(4.3. 


6.2) 


(3. 


1.8) 


(3.5. 


2.5) 


(3.4. 


3.3) 



Loads and Construction Research 

Technique 
Mathematics Research Technique 
Operating Problems Research 

Technique 
Propulsion Research Technique 
Reynolds Number Effects, Complete 

Wings (1. 2. 2. 5) 

Reynolds Number Effects - Wing 

Sections 
Riveted Connections 
Rocket Engines 
Rocket Engines, Combustion 
Rocket Fuels 
Rockets 
See 
Rocket Engines 
Rolling Contact Surfaces 
See also 
Antifriction Bearings 
Rotating-Wing Aircraft 
See also 
Autogiros 
Helicopters 
Rotating Wing Loading 
Rotating Wing Theory 
Rotating Wings 
See also 
Rotating Wing Theory 
Rotating Wings, Ej^erimental Studies 
Rotating Wings, Experimental Studies 
See also 
Rotating Wings, Power Driven 
Rotating Wings, Power Driven (1. 6. 

Rotors, Jet-Driven (3. 



(3. 8. 3) 



(1.7.3). 



(4.1.1.4) 

(1.6.1) 

(1.6) 



(1.6.2) 



1) 
9) 



(7.1) 



(5. 1. 11) 

4.1.4.1) 

(2 



3) 



Safety, Operations 
See also 
Pilot-Escape Techniques 
Sandwich Materials 

Scoops (1 

Seaplane Hull Variables 
See also 
Chines, Seaplane Hulls 
Deadrise, Sieaplane Hulls 
Length-Beam Ratio, Seaplane Hulls 
Steps, Seaplane Hulls 
Seaplanes (1. 7. 4) 

See also 
General Studies, Seaplanes 
Section Theory 
See 
Wing Section Theory 
Section Variables, Wing Sections (1. 2. 1. 2) 

See also ' 

Camber, Wing Sections ' 



Inlets and Exits, Wing Sections 

Surface Conditions, Wing Sections 

Thickness, Wing Sections 

Thickness Distribution, Wing 
Sections 
Sections, Wing 
See 

Wing Sections 
Shape Variables, Bodies 
See also 

Cross Section, Bodies 

Fineness Ratio, Bodies 

Protuberances, Bodies 

Surface Conditions, Bodies 

Thickness Distribution, Bodies 
Shear Properties of Material 
Shear in Structures 
Shells, Structural 
See also 

Cylinders, Structural 
Side Exits, Ducted Bodies 
Side Inlets, Ducted Bodies 
Sleeve Bearings 
Sliding Contact Surfaces 
See also 

Sleeve Bearings 
Sliding and Rolling Contact Surfaces 
Slipstream, Propellers 
Slots and Slats, Complete Wings 
Spinning 

Spoilers, Controls - Complete Wings 
Spoilers, Controls - Wing Sections 
Stability, Aerodynamic 
See also 

Dynamic Stability 

Static Stability 
Stability and Control, Aerodynamic 
See also 

Automatic Stabilization 

Control, Aerodynamic 

Flying Qualities 

Mass and Gyroscopic Problems, 
Aerodynamic 

Spinning 

Stability, Aerodynamic 

Stalling 

Tumbling 
Stability and Control, Hydrodynamic 
See also 

Longitudinal Stability and Control, 
Hydrodynamic 
Stalling 
Static Stability 
See also 

Directional Stability, Static 

Lateral Stability, Static 

Longitudinal Stability, Static 
Steady Loads, Tail 
Steady Loads, Wing 



(1. 3. 2) 



(5.2.6) 

(4. 3. 7. 5) 

(4. 3. 5) 



(1.3.4.4) 

(1.3.4.3) 

(3. 8. 2. 1) 

(3.8.2) 



(3.8.4) 

(1.5.4) 
(1. 2. 2, 3. 2) 

(1.8.3) 
(1.2.2.4.2) 
(1.2.1.5.2) 

(1. 8. 1) 



(1.8) 



(2. 10) 



(1.8.4) 
(1.8.1.1) 



(4. 1. 1. 2. 1) 
(4. 1. 1. 1. 1) 



194 







Subject 




Subject 






Heading 




Heading 


Subject Heading Outline 




Number 


Subject Heading Outline 


Number 


Steels 




(5. 1. 3) 


Trusses, Frames, and Gridworks 


(4.3.2) 


Steps, Seaplane Hulls 




(2. 3. 3) 


Tumbling 


(1.8.7) 


Strain Gages 






Turbine Blade Materials 




See 






See 




Instruments 






Ceramics 




Stress -Rupture Properties of 






Heat -Resisting Alloys 




Materials 




(5.2.4) 


Protective Coatings 




Stress and Vibration, Compressors 




(3. 6. 2) 


Steels 




Stress and Vibration, Turbines 




(3. 7. 3) 


Turbine Cooling 


(3. 7. 2) 


Stresses and Loads, Structural 






Turbine Disk Materials 




See 






See 




Loads and Stresses, Structural 






Heat -Resisting Alloys 




Structural Properties of Materials 




(5. 2. 9) 


Steels 




Structures 




(4.3) 


Turbine Engines 




See also 






See 




Beams, Structural 






Propulsion Systems, Complete 




Columns, Structural 






Turbine Engines, Combustion 


(3. 5. 2. 2) 


Connections, Structural 






Turbine Engines, Fuels 


(3. 4. 3. 2) 


Frames, Gridworks, and Trusses 






Turbine Flow Theory and Experiment 


(3.7.1) 


Loads and Stresses, Structural 






See also 




Plates, Structural 






Axial -Flow Turbines 




Shells, Structural 






Radial -Flow Turbines 




Submerged Inlets 


(I 


.4.1.4.2) 


Turbine-Propeller Engines, Control 


(3.2.4) 


Subsonic Diff users 


(1. 


.4.2.1.1) 


Turbine -Ram -Jet Engines, Control 


(3. 2. 3) 


Subsonic Flow 




(1. 1. 2. 1) 


Turbines 


(3.7) 


Supersonic Diffusers 


(1 


. 4. 2. 1. 2) 


See also 




Supersonic Flow 




(1.1.2.3) 


Matching, Turbines 




Surface Conditions, Bodies 




(L3.2.4) 


Stress and Vibration, Turbines 




Surface Conditions, Complete Wings 


(1 


.2.2.2.6) 


Turbine Cooling 




Surface Conditions, Friction and 






Turbine Flow Theory and Experiment 


Lubrication 




(3.8.1.3) 


Turbo -Propeller Engines 


(3.1.4) 


Surface Conditions, Wing Sections 


(1 


.2.1.2.5) 


Turbojet Engines 


(3.1.3) 


Surface Craft 




(2.8) 


Turbojet Engines, Control 


(3. 2. 2) 


Sweep, Complete Wings 


(1 


. 2. 2. 2. 3) 


Turbulent Flow 
Turbulent-Flow Combustion 


(1.1.3.2) 
(3. 5. 1. 2) 



Tail-Body Combinations, 
Tail Loads 

See 
Loads, Tail 
Tail-Wing-Fuselage Combinations - 

Airplanes 
Taper and Twist, Complete Wings 
Tensile Properties of Materials 
Thermal Properties of Materials 
Thermodynamic Properties of Gases 
Thickness, Wing Sections 
Thickness Distribution, Bodies 
Thickness Distribution, Wing Sections 
Thrust Augmentation 

See 
Auxiliary Booster Systems 
Thrust Augmentors and Pumps, Jet 
Torsion in Structures 
Transient Dynamic Loads and 

Stresses 



Missiles (1.7.2.1.2) 



(1. 
(1. 

(1. 
(1. 


, 7. 1. 1. 3) 

.2.2.2.4) 

(5.2.1) 

(5.2.11) 

(3. 11. 2) 

. 2. 1. 2. 2) 

(1.3.2.3) 

. 2. 1. 2. 3) 




(1.4.4) 
(4. 3. 7. 4) 


(4 


. 3. 7. 7. 2) 



Vibration and Flutter (4. 2) 

See also 
Vibration and Flutter, Bodies 
Vibration and Flutter - Propellers, 

Fans and Compressors 
Vibration and Flutter - Rotating- 

Wing Aircraft 
Vibration and Flutter, Tails 
Vibration and Flutter, Wings and 
Ailerons 
Vibration and Flutter, Bodies (4. 2. 3) 

Vibration and Flutter - Elevators and 

Rudders (4. 2. 2. 1) 

Vibration and Flutter - Propellers, 

Fans and Compressors (4. 2. 4) 

Vibration and Flutter, Propulsion (3. 13) 

Vibration and Flutter - Rotating- 

Wing Aircraft (4. 2. 5) 

Vibration and Flutter, Tails (4. 2. 2) 



195 



Subject Heading Outline 



Subject 

Heading 

Number 



Subject Heading Outline 



Subject 

Heading 

Number 



See also 
Vibration and Flutter, Elevators 
and Rudders 
Vibration and Flutter, Wings and 

Ailerons 
Vibration and Stress, Compressors 
Vibration and Stress, Turbines 
Viscous Flow 
See also 
Jet Mixing 
Laminar Flow 
Turbulent Flow 



W 



Wake, Complete Wings 

Wake, Wing Sections 

Wind Tunnels 

Windshields Ice Prevention and 

Removal 
Wing-Body Combinations, Missiles (1 
Wing-Fuselage Combinations, Airplanes(l 
Wing Loads 
See 

Loads, Wing 
Wing-Nacelle Combinations, Airplanes(l. 7 
Wing -Section Theory (1 

Wing Sections 
See also 

Boundary Layer, Wing Sections 

Controls, Wing Sections 

Designated Profiles, Wing Sections 

High-Lift Devices, Wing Sections 

Mach Number Effects, Wing Sections 

Reynolds Number Effects, Wing 
Sections 

Section Variables, Wing Sections 

Wake, Wing Sections 

Wing-Section Theory 



Wing-Tail-Body Combinations, 

Missiles 
Wlng-Tall-Fuselage Combinations 

Airplanes 
(4. 2. 1) Wing Theory, Complete Wings 

(3.6.2) Wing Variables, Complete Wings 
(3. 7. 3) See also 

(1. 1. 3) Aspect Ratio, Complete Wings 
Dihedral, Complete Wings 
Profiles, Complete Wings 
Surface Conditions, Complete 

Wings 
Sweep, Complete Wings 
Taper and Twist, Complete Wings 
Wings, Vibration and Flutter 
Wings 
See also 
(1.2.2.7) Wing Sections 

(1.2.1.9) Wings, Complete 

(9.1.1) Wings and Tails, Ice Prevention and 

Removal 
Wings, Complete 
See also 
Boundary Layer, Complete Wings 
Controls, Complete Wings 
High-Lift Devices, Complete Wings 
Mach Number Effects, Complete 

Wings 
Reynolds Number Effects, Complete 
(1. 2. 1) Wings 

Wake, Complete Wings 
Wing Theory, Complete Wings 
Wing Variables, Complete Wings 
Woods 



(7. 
7.2. 
7.1. 



2.7) 
1.9) 
1.1) 

3.4) 
1.1) 
1.1) 



1.2) 
1.1) 



(1.7.2.1.4) 

(1, 7. 1. 1. 3) 
(1. 2. 2. 1) 
(1. 2, 2. 2) 



(4.2.1) 
(1.2) 



(7. 3. 3) 
(1.2.2) 



(5. 1. 7) 



Yaw and Pitch, Propellers 



(1.5.2.9) 




AUTHOR INDEX 



197 



Abbott, Frank T., Jr., 108 

Adams, James J. , 14, 28, 97, 147 

Aiken, William S. , Jr. , 76 

Alexander, Sidney R. , 3, 16(2), 26 

Alford, William J. , Jr. , 15, 23, 28, 30 

Allen, Edwin C, 43 

Allen, Hubert W., 3(2) 

AUis, Arthur E. , 62 

Amer, Kenneth B. , 3, 80 

Anderson, Roger A., 150 

Anderson, Seth B. , 20, 29, 36 

Anderson, Warren E. , 57 

Anderson, William J. , 131(2) 

Angle, EUwyn E. , 90 

Ankenbruck, Herman O. , 76 

Armstrong, JohnC, 120, 122 

Arne, Vernon L. , 3 

Ashkenas, Harry, 1 

Assadourian, Arthur, 97 

Axelson, John A. , 4 

Axilrod, Benjamin M. , 157 



B 



Bailey, Frederick J. , Jr. , 5 

Baker, John E., 7, 62 

Bandettini, Angelo, 32 

Bandish, Rozalia M. , 23 

Barclay, F. Dorn, 53 

Barling, Walter H. , Jr. , 47 

Barlow, William H. , 82 

Barnes, Robert H. , 36 

Barson, Zelmar, 123 

Barzelay, Martin E. , 151 

Bates, William R. , 51, 69 

Baughman, L. Eugene, 46, 56 

Beam, Benjamin H. , 91 

Beard, Luther, Jr. , 32 

Becht, Robert E. , 25(4), 26, 27(2), 29 

Beck, Paul A. , 156 

Becker, R. , 13 

Beckhardt, Arnold R. , 45 

Beckwith, Ivan E. , 7 

Beeler, De Elroy, 42, 74 

Belles, Frank E. , 124 

Bellman, Donald R., 43, 125 

Bennett, Charles V. , 74, 75 

Berggren, Robert E. , 22(2) 

Berlad, Abraham L. , 124(2) 

Berman, Julian H. , 26 

Berman, Theodore, 104 

Bernstein, Harry, 6 

Bingham, Gene J. , 55, 56 

Bird, John D. , 92, 93 

Bisson, Edmond E. , 131 

Bittker, David A., 126 

Blackaby, James R. , 53 

Bland, William M. , Jr. , 94 



Blatz, Robert E. , 12 

Bobbitt, Percy J., 7 

Boddy, Lee E. , 27 

Boeckh, 146 

Boegli, J. S. , 133 

Bonneville, JC M. , 131 

Booth, Robert A. , 21 

Boswinkle, Robert W. , Jr. , 16 

Bowden, Dean T. , 12 

Boyd, JohnW., 21(2) 

Brajnikoff, George B., 53(2), 55, 56 

Branstetter, J. Robert, 125 

Bray, Richards., 29(2),^ 75 

Brevoort, Maurice John, 4, 6, 7 

Brightwell, Virginia L. , 80 

Brinieh, Paul F. , Jr. , 7 

Bromm, August F. , Jr. , 6(2) 

Brooks, George W. , 67(3) 

Brooks, William A., Jr., 150 

Brown, Beverly Porter, 35(2), 74, 174 

Brown, Clinton E. , 22 

Brown, Harold A. , 176 

Brown, Harvey H. , 34, 39 

Brown, Stuart C. , 76 

Brown, W. Byron, 120 

Brun, Rinaldo J. , 16, 77(2) 

Bryant, Robert L. , 25, 91 

Buchele, Donald R., 182 

Budiansky, Bernard, 21, 145, 150 

Buell, Donald A., 64 

Burk, Sanger M. , Jr., 38, 104 

Bursnall, William J. , 8 

Butler, Roger V. , 112 

Byrnes, Andrew L. , Jr. , 15 



Cahill, Jones F. , 17, 33, 92 
Callaghan, Edmund E. , 59, 123 
Campbell, George S. , 21, 41 
Campbell, John P. , 87 
Canning, Thomas N. , 39, 46(2) 
Cannon, Michael D. , 62 
Carmel, Melvin M. , 63(2) 
Carroll, Raymond B. , 9, 58 
Carroll, Robert W. , 60 
Carros, Robert J. , 6 
Carter, Arthur W. , 112 
Caywood, William C, 120 
Chambliss, Derrill B. , 113 
Chapman, Dean R. , 2, 16, 17 
Charters, Alex C. , Jr., 90 
Chauvin, Leo T. , 3, 12, 78 
Cheesman, Gail A. , 17 
Chiarito, Patrick T. , 21 
Chilton, Robert G. , 91, 174 
Christopher, Kenneth W. , 114(2) 
Clagett, Harry P. , 76 
Clark, Thomas P. , 124, 126 
Cleary, Joseph W. , 21, 34 



198 



Clevenpon, Sherman A. , 145, 147 

dousing, Lawrence Adrian, 34, 39 

Coale, C. W., 145 

Coffin, Kenneth P. , 124 

Cohen, Clarence B. , 2(2) 

Cohen, Doris, 7 

Cohen, Nathaniel B. , 8 

Cole, Isabella J. , 6 

Cole, Richard I., 49 

Coleman, Thomas L. , 142(2) 

Coles, WillardD., 12, 59 

Coletti, Donald E., 6 

Coiner, William H. , 155 

Comisarow, Paul, 26 

Connors, J. F. , 55 

Cook, Francis E. , 145 

Cooney, T. V., 76, 77 

Cooper, George E. , 36, 75, 76 

Cooper, Morton, 6 

Copp, Martin R. , 55, 142 

Coppolino, Domenic A. , 63 

Corrsin, Stanley, 1(2) 

Costello, George R. , 8 

Crane, Harold L., 14, 28, 34, 35, 45 

Creer, Brent Y. , 92 

Crigler, John L. , 62 

Crim, Aimer D. , 67, 81 

Critzos, Chris C, 16 

Croom, Delwin R. , 33, 37 

Cummings, John L. , 5, 46 

Cunningham, Herbert J. , 1, 30 

Curfman, Howard J. , Jr. , 16, 92 

Czarnecki, Kazimierz Roman, 5(2), 6, 8(2) 



D 



Daley, Bernard N. , 3, 4 

Danforth, Edward C. B. , 3d., 3, 4, 21, 50, 176 

Dannenberg, Robert E. , 8, 16, 17 

Davenport, Edwin E. , 32(2) 

Davids, Joseph, 55 

Davidson, Robert E. , 62(2) 

Davis, Wallace Frederick, 53, 56 

Dawson, John Robert, 113 

Deissler, Robert G. , 11, 133 

Delano, James B. , 62(2), 63(2) 

Delany, Noel K. , 32(2), 53 

Delio, Gene J. , 122 

DeMoraes, Carlos A., 12, 50 

Denardo, Billy Pat, 39 

Dennis, David H. , 5 

DeRocher, Wilfred L., Jr., 121 

Deutsch, George C, 156 

Dewey, Paul E. , 54(2) 

DeYoung, John, 47 

Dhawan, Satish, 1 

Diaguila, Anthony J. , 11 

Dick, Richards., 4 

Diederich, Franklin Wolfgang, 86, 145 

Diederich, Margaret S. , 21 



Dieter, George Ellwood, Jr. , 155 
Dietz, Albert E., 22 
Dietz, O., 146 
Dingeldein, Richard C. , 67 
Dittrich, Ralph T. , 124 
Dods, Jules B. , Jr. , 30 
Donaldson, Coleman duPont, 2, 9 
Donegan, James J. , 91 
Donlan, Charles J. , 71 
Donoughe, Patrick L. , 8, 11, 12 
Doring, Werner, 13 
Dorsch, Robert G. , 77(2) 
Dosanjh, Darshan Singh, 177 
Douglass, Howard W., 124(2) 
Dow, Nor r is F. , 151 
Drake, Hubert M. , 74(4), 75, 76 
Drake, WrayV., 131 
Draper, John W. , 32(4), 72 
Drell, Isadore L. , 131 
DuBois, George B. , 131(2) 
Dugan, Duane W. , 4, 22 
Dugger, Gordon L. , 124 
Dumas, R. , 9, 10 
Dunning, Robert W. , 4, 24 



E 



Eaton, I. D. , 151 

Eckert, Ernst Rudolf Georg, 11(2), 12 

Edge, Philip M. , Jr. , 145 

Edmondson, James L. , 15, 22(2) 

Eggers, A. J. , Jr. , 5 

Eggleston, John M. , 75, 76 

Ellis, Macon C . , Jr. , 5 

Elwell, FredS. , 170 

Engel, Jerome N. , 142 

Erickson, Albert L. , 25 

Ernst, Edward A., 36 

Esgar, JackB., 120 

Eubanks, A. G. , 157 

Evans, Albert John, 6, 62(3) 

Evvard, JohnC, 58 



Faber, Stanley, 28, 91 

Faget, Maxime A. , 58 

Farmer, James Elmo, 129 

Favre, Alexandre, 9, 10 

Feiler, Charles E. , 125 

Fenn, David B. , 55 

Fenn, "Virginia O. , 124 

Ferrari, Carlo, 7 

Ferri, Antonio, 53 

Few, Albert G. , Jr. , 25(3), 26, 27 

Fields, Edison M. , 35 

Fieno, Daniel, 121 

Fikes, Joseph E. , 28, 29(2), 30(2), 33, 36 



199 



Fink, Marvin P. , 28 
Fischel, Jack, 25, 32, 37 
Fisher, Lewis R. , 73 
Fletcher, Herman S. , 73 
Fliigge, Wilhelm, 145 
Fontana, Rudolph E. , 23 
Forestieri, Americo F. , 160 
Forsyth, Charles M. , 74 
Foss, Kenneth A. , 86 
Foster, John V. , 176 
Fournier, Paul G. , 23(3) 
Fox, Jerome L., 5 
Francis, Howard T. , 155 
Francisco, Allen C. , 151 
Frank, Joseph L. , 53, 54 
Frazer, Alson C. , 57 
Freche, John C, 129 
Freeman, James W. , 155 
Frenkel, Ya I. , 158 
Frick, Charles W. , 21(2) 
Fricke, Clifford L. , 12 
Friedman, Morris D. , 7 
Fryer, Thomas B. , 93 
Fuller, Franklyn B. , 7, 22 
Fung, Yuan-Cheng, 150 
Funk, Jack, 30 
Furlong, G. Chester, 27 



Gale, Lawrence J. , 2, 49, 72, 75 
Gallagher, Helen M. , 16 
Gambucci, Bruno J. , 8 
Gardner, William N. , 16, 45 
Garrett, Floyd B. , 55, 120(3), 156 
Gates, Ordway B. , Jr. , 78 
Gaviglio, J., 9, 10 
Gelder, Thomas F. , 16 
George, Desmond A. , 157 
Germain, Paul, 7 
Gerstein, Melvin, 125 
Gessow, Alfred, 67(3) 
Gilman, Jean, Jr., 62(3) 
Glawe, George E. , 161 
Godfrey, Douglas, 131 
Goin, Kennith L. , 6, 33 
Gold, Harold, 121, 122 
Goldstein, Arthur W. , 7 
Goldstein, David L., 56 
Gomberg, Henry J. , 155 
Goodman, Harold R., 36, 74 
Goodson, Kenneth W., 21, 27(3) 
Goodwin, Julia M. , 7 
Goodwin, Roscoe H. , 49, 68 
Gortler, Henry, 8 
Gottlieb, Stanley M. , 100 
Gould, Lawrence I. , 56 
Gracey, William, 176 



Graham, Donald J. , 16 
Grala, E. M. , 156 
Grant, Frederick C. , 6 
Grape, Richard G. , 2 
Graves, , Charles C. , 125 
Gray, Lyle J. , 34 
Gray, Vernon H. , 12 
Gray, Wilbur H. , 62(2), 64 
Gregg, John L. , 5 
Griffith, John H. , 43 
Grigsby, Carl E. , 5 
Grover, Horace John, 
Gundzik, Richard M. , 
Gyorgak, Charles A. , 



155 
125 
120, 



151, 156(2) 



H 



Habel, Louis W. , 20 

Hadlock, IvanK., 142 

Haefeli, Rudolph C. , 5, 6 

Hagerman, John R. , 27, 29, 35 

Hagginbothom, W. K. , 59 

Hall, Albert W. , 15(2), 24, 28 

Hall, Charles F. , 53(2) 

Hamaker, Frank M. , 7 

Hamilton, Clyde V. , 6 

Hammond, Alexander D. , 30(2), 32, 35(2), 36 

Hamrick, Joseph T. , 2 

Hansen, Arthur G. , 8 

Hardrath, Herbert F. , 152 

Harling, R. , 146 

Harp, James L. , Jr. , 120 

Harper, Paul W. , 68 

Harrington, Robert D. , 51 

Harrison, Daniel E. , 62, 63 

Harrison, William N. , 156(2) 

Hart, H. A., 62 

Hart, Roger G. , 50 

Hartmann, E. C. , 151 

Hasel, Lowell E. , 6 

Hassell, James L. , Jr. , 92 

Hayes, William C. , 49 

Hayter, Nora-Lee F. , 29, 32(2) 

Hazen, Marlin E. , 67 

Heaslet, Maxwell Alfred, 7, 22 

Heath, Atwood R. , Jr. , 148 

Hedgepeth, John M. , 46 

Heimerl, George J. , 155 

Heinle, Donovan R. , 31 

Heitkotter, Robert H. , 121 

Hemenover, Albert D. , 16 

Henderson, Arthur, Jr. , 7 

Henney, Floyd W. , 14 

Hennings, Glen, 121 

Hermann, R. , 133 

Herzig, Howard Z. , 3, 8 

Heyson, Harry H. , 16, 47 

Hibbard, Robert R. , 124 

Hikido, Katsumi, 22 



200 



Hill, Paul R. , 80, 90 

Killer, Kirby W. , 122 

Hilton, John H. , Jr. , 6, 8 

Hipsher, Harold F., 124 

Hofstetter, Robert U. , 179 

Holleman, Euclid C. , 90 

HoUoway, George F. , 151 

Holt, Marshall, 151 

Holzhauser, Curt A. , 49, 54, 56(2) 

Hood, Richard, 122 

Hopkins, Edward J. , 7 

Home, G. T. , 155 

Home, Walter B. , 145, 146 

Houbolt, JohnC, 146 

Howell, Robert R. , 54 

Howes, Walton L. , 182 

Hubbard, Harvey H. , 11, 62, 80 

Hubbartt, James E. , 3 

Hughes, Philip J., 155(2) 

Hultz, Burton E. , 38 

Humphrey, JackC, 125 

Humphreys, Milton D. , 4(4), 14 

Hunczak, Henry R. , 11 

Hunt, Robert M. , 62 

Huppert, Merle Cecil, 121 

Hyler, Walter S. , 155 



Igoe, William B. , 62 
lUg, Walter, 152 
Inge, John E. , 155 
Ingebo, Robert D. , 133 
Intrater, J., 155(2) 



Jack, John R. , 8 

Jackson, H. Herbert, 6, 78 

Jackson, Joseph L. , 124 

Jacques, James R. , 121 

Jagger, James M. , 5(2) 

James, Carlton S. , 6 

Jaquet, Byron M. , 23, 25, 29 

Jedlicka, James R. , 6 

Johnson, Aldie E. , Jr. , 150, 157(2) 

Johnson, Harold I., 23, 31, 35(2), 36, 37 

Johnson, Harold S. , 35(2), 49 

Johnson, Joseph L. , Jr. , 30, 33, 34, 47, 73 

Johnson, Peter J. , 62 

Johnson, R. D. , 155 

Johnson, Robert L. , 131(4) 

Johnston, J. Ford, 3(2) 

Jonash, Edmund R. , 124 

Jones, Ira P. , Jr. , 75, 84 

Jordan, Gareth H. , 21 

Joyner, Upshur Tucker, 145 



Kaplan, A., 150 

Kaplan, Carl, 2(2), 3 

Katz, Ellis R. , 17, 23, 51 

Katz, N. H., 156 

Katzen, Elliott D. , 21 

Kaufman, Albert, 120 

Kaufman, Samuel J., 121 

Keener, EarlR., 23(3) 

Keith, ArvidL., Jr., 30, 55, 56 

Kell, Robert J., 46 

Kelly, John A., 7, 17, 29 

Kemp, William B. , Jr. , 21, 23, 25(3), 26 

Kennedy, Robert M. , 28, 72(3) 

Kennedy, Thomas L. , 80, 90 

Kent, John D. , 4 

Kester, Robert H. , 16 

Keune, Friedrich, 14 

King, Douglas A. , 114, 116 

King, Thomas J. , Jr. , 25, 27(2), 31, 41 

Kirkpatrick, H. B. , 156 

Kistler, Alan L. , 1 

Klebanoff, Philip Samuel, 10 

Klinar, Walter J. , 84 

Knechtel, Earl D. , 28 

Kochendorfer, Fred D. , 5 

Kofskey, Milton G. , 3(2) 

Kolk, W. Richard, 24, 73 

Kordes, Eldon E. , 147 

Kotanchik, Joseph N. , 21 

Kraft, Christopher C, Jr., 47, 97 

Kramer, James J. , 1(2) 

Kranz, M. , 145 

Krebs, Richard P. , 80 

Kremzier, Emil J. , 55 

Krumm, Walter J. , 24 

Kruszewski, Edwin T. , 147 

Kuehn, Donald M. , 179 

Kuhn, Richard E., 27(2), 32(4), 35, 73 

Kvihns, Perry W., 121 

Kurbjun, MaxC, 31, 51, 64 

Kyle, James C, 21 



Ladanyi, Dezso Joseph, 121 

Lamneck, John H. , Jr. , 124 

Land, Norman Stafford, 108, 113, 116 

Lange, Roy H. , 28, 35 

Lanzo, Chester D. , 123 

Lassiter, Leslie W. , 11, 62, 80, 121 

Lauten, William T. , Jr. , 2, 69 

Lawrence, Leslie F. , 71 

Lazar, James, 121 

Leonard, Robert W. , 145 

Lessing, Henry C, 93 

Letko, William, 27, 50 



201 



Levy, Lionel L. , Jr. , 28 

Lewis, R. A. , 155 

Lichtenstein, Jacob H. , 23 

Liddell, Charles J. , Jr. , 92 

Liepmann, Hans Wolfgang, 8 

Lietzke, Armin F. , 133 

Lilly, Howard C, 82 

Lina, Lindsay John, 4, 26, 176(2) 

Lindqulst, Dean C. , 139, 145 

Lindsey, Walter FranJi, 5 

Liner, George, 62 

Lipsitt, H. A. , 155 

Livingood, John N. B. , 8, 11, 12 

Lockwood, VernardE., 18, 27, 28(2), 29, 30(2), 

33, 35(2), 36 
Loftin, Laurence K. , Jr. , 14, 15(2), 17 
Lomax, Harvard, 22(2), 142 
Long, Roger A. , 129, 155 
Look, Bonne C . , 28 
Lopatoff, Mitchell, 3, 4 
Loposer, J. Dan, 1, 9, 10 
Lord, Albert M. , 125 
Lord, Douglas R. , 3 
Love, Eugene S. , 4, 6, 22 
Loving, Donald L. , 74 
Low, George M. , 2 
Lowdermilk, Warren H. , 133 
Lowry, John G. , 29 
Lubarsky, Bernard, 121 
Luchuk, Wallace, 62 
Lundstrom, Reginald R. , 1, 168 
Luoma, Arvo A. , 25 



M 



Mc and Mac 

Surnames beginning with Mc or Mac are all 
filed as if spelled Mac. 



McCarty, John Locke, 67 
McComb, Harvey G. , Jr. , 150, 151 
McCullough, George Burns, 7, 17 
McDevitt, JohnB., 4(2), 24 
McDonald, GlenE., 124(2) 
McEvily, Arthur J., Jr., 155(2) 
McFadden, Norman M. , 29 
McFall, JohnC, Jr., 52 
McGehee, John R. , 112 
McKay, James M. , 15, 24, 
McKinney, Marion O. , Jr. , 
McKinnon, Roy A. , 12 
Macks, Elmer Fred, 131 
McLaughlin, Milton D. , 34, 
McLellan, Charles Herbert, 
McLemore, Huel Clyde, 62 
MacLeod, Richard G. , 29, 36, 
MacNeal, Richard H. , 151 
McNeill, Walter E. , 76 
Maki, Ralph L. , 33 
Male, Theodore, 125 



28, 40, 
32 



68 
6 



43 



50 



Malick, Alexander W. , 32, 34, 37 

Mandel, J., 157 

Manson, Samuel S. , 129, 156 

Margolis, Kenneth, 6, 7 

Marte, Jack E. , 8 

Martin, Andrew, 21 

Martin, John C. , 1 

Martin, Norman J. , 57(2) 

Martina, Albert P. , 22, 29 

Maslen, Stephen H. , 11 

Mason, Homer P. , 45 

Mathauser, Eldon E. , 150, 151 

Matheny, Cloyce E. , 45 

Mathews, Charles W. , 1, 3, 15, 74, 97 

Matthews, Clarence W. , 2 

Matthews, James T. , Jr. , 40, 74, 75 

Mattson, Axel T. , 39, 74 

Maxwell, William A., 155, 156(2) 

Mayer, John P. , 3, 74 

Mayers, J. , 150 

Maynard, Julian D. , 62 

Mazelsky, Bernard, 142 

Mead, Merrill H. , 93 

Meadows, May T. , 142 

Mehl, Robert Franklin, 155 

Melzer, M. , 146 

Mendelson, Alexander, 60 

Merlet, Charles F. , 53 

Metzger, M. ,^ 155(2) 

Meyer, Andre J. , Jr. , 120 

Michael, William H. , Jr. , 22 

Mickleboro, Harry C, 30 

Mickley, H. S. , 1 

Miele, Angelo, 77 

Migotsky, Eugene, 2 

Millenson, Morton B. , 129 

Miller, Riley O. , 121 

Milling, Robert W., 63 

Milwitzky, Benjamin, 139, 145 

Mirels, Harold, 5(2), 9, 46 

Mitcham, Grady L. , 69 

MitcheU, Jesse L, , 176 

Moeckel, WoKgangE., 4, 55 

Molk, Ashley J. , 55 

Moore, Dwight G. , 156(2), 157 

Moore, Franklin K. , 2, 11 

Moore, John A. , 7 

Mordfin, Leonard, 150 

Morduchow, Morris, 2 

Morgan, Francis G. , Jr. , 62, 63 

Morgan, William C. , 120 

Morris, Garland J., 15, 28, 29, 72(2), 176 

Morrison, William D. , Jr., 23(3), 27(2), 41 

Morrow, John D. , 17(2) 

Morse, C. Robert, 120 

Moseley, William C, Jr., 25, 30, 33 

Moskowitz, Barry, 8 

Mossman, Emmet A. , 54 

Mottard, Elmo J. , 1 

Mueller, James N. , 5(2) 

Mungall, Robert G. , 31 



202 



Murphy, Maurice P. , 62 

Murray, S. F. , 131(2) 

Myers, BoydC, 2d., 27(4), 35, 41, 42 



N 



Naeseth, Rodger L. , 51 

Nason, Martin L. , 78 

Neel, Carr B. , Jr. , 165(2) 

Neihouse, Anshal I. , 29 

Nelson, Herbert C, 26 

Nelson, Robert L. , 26 

Nelson, Walter C. , 78 

Nelson, Warren Howard, 24(2), 25 

Nelson, William J. , 54 

Nemeth, ZoltonN., 131(2) 

Nichols, Mark R. , 54 

Nielsen, Helmer V. , 6 

Nitzberg, Gerald E. , 7 

North, Warren J., 123 

Nuber, Robert J. , 17 

Nucci, Louis M. , 5, 53 



Petynia, William W. , 113 

Phelps, E. Ray, 4 

Phillips, William E. , Jr. , 122 

Phillips, William H., 147 

Pierce, Mary, 23 

Pierpont, P. Kenneth, 54(2) 

Pinkel, Benjamin, 156 

Pinkel, I. Irving, 5, 120 

Pitkin, Marvin, 16 

Pittel, Murray, 21 

Pitts, Joseph W., 156 

Piatt, Robert J., Jr., 63(2) 

Polhamus, Edward C, 2, 22, 25, 29, 31, 41, 75 

Potter, A. E., Jr., 124 

Potter, Dexter M. , 139, 145 

Powell, Robert D., Jr., 17 

Prasse, Ernst I. , 11 

Press, Harry, 46, 142(2), 146 

Preston, George Merritt, 120 

Prosser, Stanley B. , 155 

Pumphrey, Norman E.,,, 72 



Q 



Queijo, Manuel J. , 68 



Oberndorfer, Gale C. , 33 

O'Brien, Vivian, 1 

O'Bryan, Thomas C. , 4, 71, 176(2) 

Ocvirk, FredW., 131(2) 

O'Hare, William M. , 27, 37, 76 

O'Kelly, Burke R. , 168 

Olson, Robert N. , 71 

O'Neal, Cleveland, Jr., 124 

Oppenheimer, Frank L., 121 

Osborne, Robert S. , 5 

Otto, Edward W., 122 



Pack, George J. , 120 
Page, William A. , 16 
Fappas, Constantine C. , 6 
Paradiso, Nicholas J. , 16, 29 
Pasamanick, Jerome, 28 
Passera, Anthony L. , 78(3) 
Pasteur, Thomas B. , Jr. , 41 
Paulson, John W. , 30 
Pearson, Albin O. , 176(2) 
Peck, Robert F. , 51, 176 
Peele, James R. , 23 
Pendley, Robert E. , 53(2) 
Peres, M. J. , 7 
Perkins, Edward W. , 46(2) 
Pesman, Gerald J. , 120 
Peters, Max D. , 80 
Peters, Roger W. , 151 
Peterson, James P. , 150 
Peterson, Marshall B. , 131 



R 



Racisz, Stanley Frank, 29 

Rainey, A. Gerald, 26, 30 

Rainey, Robert W. , 4 

Rainey, Ruby A., 26 

Ramsen, John Albert, 17, 26, 50, 53 

Rashis, Bernard, 6, 7 

Rathert, George A., Jr., 29, 34, 36, 54 

Rayle, Warren D. , 124 

Reed, James F. , 21 

Reed, Verlin D. , 32 

Reed, Wilmer H. , 3d. , 4 

Reese, James R. , 74 

Regier, Arthur A. , 7 

Reller, John O. , Jr. , 7 

Rennemann, Conrad, Jr. , 7 

Reshotko, Eli, 2(2), 7 

Resnikoff, Meyer M. , 5, 6 

Reynolds, Robert M. , 55, 64 

Ribner, Herbert Spencer, 6(2) 

Richmond, Joseph C. , 156 

Riddell, Frederick Raymond, 1 

Rideout, Sheldon Paul, 156 

Riebe, John M. , 50, 51 

Rightmire, Brandon Garner, 131 

Riley, Donald R. , 68(2) 

Ritchie, Virgil S. , 2 

Robards, Chester F. , 120 

Robinson, Harold L. , 46, 53(2) 

Robinson, Ross B. , 8 

Rockett, John A. , 114 

Roden, William S. , 75, 76 



203 



Rodert, Lewis August, 55 

Rogallo, Vernon L. , 64 

Rogers, Arthur William, 1 

Rohiik, Harold E. , 3 

Rolls, L. Stewart, 36, 39, 54 

Rosecrans, Richard J. , 151 

Rosenzweig, Solomon, 121 

Roshko, Anatol, 1(2) 

Ross, Alberto., 121 

Ross, R. C. , 1 

Rousso, Morris D. , 5, 11 

Rubesin, Morris W. , 7, 10 

Rubin, Arnold J. , 55 

Rumsey, Charles B. , 3, 7, 9, 78 

Runyan, Harry L. , 148 

Russell, Walter R. , 176 



Sabol, Alexander P. , 181 

Sacks, Alvin H. , 22 

Sadoff, Melvin, 38, 75(2), 76(2) 

Sammonds, Robert I. , 55(2) 

Sams, EldonW. , 13 

Sandahl, Carl A., 24, 34, 94(2) 

Sandborn, Virgil A., 3, 10, 11 

Sanders, E. Claude, Jr., 22 

Sanders, John C. , 80 

Sargent, Arthur F. , Jr. , 123 

Savin, Raymond C, 7 

Sawyer, Richard H. , 15, 26, 28 

Schade, Robert O. , 92 

Schafer, Louis J. , Jr., 120 

Schalla, Rose L. , 124(2) 

Scher, Stanley H. , 49(3), 82, 109(2) 

Scherrer, Richard, 21 

Schiff, Jack, 30 

Schlaefke, Karlhans, 145 

Schlechte, Floyd R. , 151 

Schmidt, Stanley F. , 103 

Schneiter, Leslie E. , 35 

Schnitzer, Emanuel, 81 

Schwartz, Ira R. , 9 

Schwartzberg, Milton Allen, 31 

Schwent, Glennon V. , 122 

Schwope, A. D. , 155 

Schy, Albert A. , 78 

Seaberg, Ernest C. , 78, 90(2), 92 

Sears, R. I. , 53 

See, John A. , 76 

Seiff, Alvin, 6(2) 

Sellers, Thomas B. , 28 

Semonian, Joseph W. , 150(2) 

Serafini, John S. , 5, 16 

Sewall, John L. , 74 

Shepard, Charles E. , 2, 161 

Shillito, Thomas B. , 120 

Shinbrot, Marvin, 90 

Short, Barbara J. , 7 

Shufflebarger, Charles C. , 46 



Shuford, Charles L. , Jr. , 23, 112(2), 114(3) 

Shumaker, Robert A. , 63 

Sikora, Paul F. , 120 

Silhan, Frank V., 53 

Silsby, Norman S., 29, 40, 43, 72(2), 145 

Silvers, H. Norman, 24, 39, 71 

Simmons, Frederick S. , 1, 12 

Simon, Dorothy Martin, 124 

Sinclair, Archibald R. , 6 

Sisk, Thomas R. , 38, 75(2) 

Skinner, George Tolmie, 8 

Sleeman, William C, Jr., 27(3) 

Slogar, Raymond J., 3, 11 

Slone, Henry O. , 3 

Sluder, Loma E. , 22 

Smiley, Robert F. , 146 

Smith, Charles C, Jr., 50 

Smith, Earl F. , 78 

Smith, Francis B. , 12 

Smith, G. Allan, 28 

Smith, Kenneth J. , 2 

Smyers, William H. , Jr. , 16 

Solomon, George E. , 4 

Solomon, Joseph, 14 

Solomon, Martin, 30 

Solomon, William, 64 

Sommer, Simon C, 5, 7 

Sorenson, Robert M. , 21 

Spangenberg, Wesley G. , 177 

Sparrow, E. M. , 9 

Spearman, M. Leroy, 26, 39 

Spiegel, Joseph M. , 6, 56, 179 

Spreemann, Kenneth P. , 23, 24, 28, 30, 39, 41 

Spreiter, John R. , 2 

Squyers, A. L. , 1 

Stalder, Jackson R. , 6 

Stanitz, John D. , 1(2) 

Stark, James A., 5 

Steinberg, Seymour, 20, 63 

Stephenson, Bertrand H. , 146 

Stepka, Francis S. , 120 

Sterbentz, William H. , 55, 58 

Sterrett, James R. , 4 

Stevens, George L. , 21 

Stevens, Kenneth N. , 170 

Stewart, W. E. , 1 

Stine, Howard A. , 8 

Stivers, Louis S. , Jr. , 32(2), 34, 37, 42 

Stokes, Fred H. , 97 

Stone, David G. , 94 

Stone, Ralph W., Jr., 91 

Stoney, William E. , Jr. , 51 

Strass, H. Kurt, 35(2) 

Strieker, Edward G. , 124 

Summers, James L. , 16, 22 

Swett, Clyde C. , Jr. , 127 

Swihart, John M. , 66 

Swikert, Max A. , 131(2) 

Sylvester, Maurice A., 2, 67(2) 

Szczeniowski, Boleslaw, 11 



204 



Talbot, L., 7 

Tapscott, Robert J. , 67 

Taylor, Maynard F. , 11 

Taylor, Robert A. , 4, 54(2) 

Teitelbaum, Jerome M. , 92 

Theisen, Jerome G. , 145 

Thibodaux, J. G. , 59 

Thompson, Jim Rogers, 1, 3(2), 15, 51, 75(2) 

Thompson, Robert F. , 27, 30, 35, 42 

Tinling, Bruce E. , 24, 73 

Toll, Thomas A., 87 

Tong, Kin Nee, 151 

Tosti, Louis P. , 32(2) 

Towe, George C. , 155 

Trant, James P. , Jr. , 38, 105, 176 

Trimpi, Robert L. , 2(2), 8 

Triplett, William C, 28, 42, 76, 103 

Truckenbrodt, Erich, 9 

Tucker, Maurice, 7, 13 

Tucker, Warren A., 15, 21 

Tulin, Marshall P. , 1, 2 

Tunnell, Phillips J. , 6 

Tuovila, Weimer J. , 7 

Turner, Howard L. , 90 

Turner, Thomas R. , 18, 27, 28, 33, 35, 36(2), 41 



U 



Uberoi, Mahinder S. , 1 
Ulmann, Edward F. , 5, 24 
Underwood, William J. , 17 
Useller, James W. , 120 



Valentine, Edwin Floyd, 9, 55, 58 

Valentine, George M. , 74 

Van Dyke, Milton Denman, 1, 3 

Van Dyke, Rudolph D. , Jr., 36, 42, 90, 92 

Varga, Steven A. , 7 

Vasu, George, 120 

Vaughan, Victor L., Jr., 17, 26 

Vick, Allen R. , 53 

Vincenti, Walter G. , 4(2) 

Vitale, A. James, 46 

Vogeley, Arthur William, 62, 64 

Vogler, Raymond D., 18, 27, 35(2), 36 

Voglewede, Thomas J. , 5 

Vogt, Dorothea E., 16 

von Doenhoff, Albert E. , 14 

Von Glahn, Uwe H. , 12, 16 



Walker, Curtis L. , 55 

Walker, Harold J. , 22, 32, 42 

Walker, John H. , 64 

Walker, Walter G. , 142(3) 

Wallner, Lewis E. , 55 

Walls, James H. , 145, 146 

Waner, Paul G. , Jr. , 46 

Wanlass, Kent, 8 

Wasserman, Robert, 7 

Watkins, Charles E. , 26, 148 

Watson, James M. , 25(3), 30(3) 

Wear, Jerrold D. , 120, 124(2) 

Weeton, John Waldemar, 120 

Wehe, R. L. , 131 

Weiberg, James A. , 8, 16, 17 

Weil, Joseph, 21, 27, 39 

Weiland, Walter F. , Jr. , 13, 133 

Weinflash, Bernard, 114(4) 

Weinstein, Maynard I. , 56 

Welsh, Clement J. , 15, 50 

Weltmann, Ruth N. , 124 

Westmoreland, J. C. , 136 

Whitcomb, Richard Travis, 21, 28(2), 62 

White, Johns., 90 

White, Maurice Donald, 28 

Whitten, James B. , 97 

Wick, Bradford H., 14 

Widmayer, Edward, Jr. , 145 

Wier, John E. , 157 

Wiggins, James W. , 42, 73 

Wilcox, WardW. , 128 

Wiley, Harleth G. , 30, 36, 37(2) 

Wilkins, Max E. , 6 

Wilks, I. Edward, 150 

Williams, Claude V. , 53 

Williams, Thomas W. , 6 

Williams, Walter C, 74(4), 75 

Wilson, Herbert A., Jr., 17 

Wilson, Jack H. , 75 

Wilsted, H. Dean, 122 

Wimbrow, William R. , 21 

Winograd, Lee, 36 

Wintler, John T. , 55 

Wolhart, Walter D. , 27 

WoUner, Bertram C, 68 

Wolock, Irvin, 157 

Wood, Charles C, 3 

Wood, John H. , 66 

Woodbridge, Julia B. , 23 

Woolley, Harold W., 11 

Wright, JohnB. , 5, 23, 25, 46, 68 

Wright, LinwoodC, 3 

Wright, Ray H. , 1, 2 

Wyatt, DeMarquis D. , 58 

Wyss, John A., 21 



W 

Wadlin, Kenneth L., 23, 53, 112, 113 
Wagoner, CleoB., 4 



Yaggy, Paul F. , 64 
Yaker, Charles, 120(2) 



205 



Yancey, Roxanah B. > 74 
Yeates, John E. , Jr. , 5 
Yntema, Robert T. , 80 
Young, A. P., 155 



Zalovcik, John A., 15, 176 
Zarovsky, Jacob, 78 
Ziemer, Robert R. , 120 
Zimmerman, Charles Horton, 90 
Zontek, Leon, 37 



NACA - Langley Field, Va.